EP3700740A1 - Method for the structural bonding of structural components, and textured-surface insert for implementing said method - Google Patents

Method for the structural bonding of structural components, and textured-surface insert for implementing said method

Info

Publication number
EP3700740A1
EP3700740A1 EP18796858.1A EP18796858A EP3700740A1 EP 3700740 A1 EP3700740 A1 EP 3700740A1 EP 18796858 A EP18796858 A EP 18796858A EP 3700740 A1 EP3700740 A1 EP 3700740A1
Authority
EP
European Patent Office
Prior art keywords
composite material
structural
textile fibers
textured surface
web
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP18796858.1A
Other languages
German (de)
French (fr)
Inventor
Jérémie Daniel PLOCINIAK
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Paradox
Original Assignee
Paradox
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Paradox filed Critical Paradox
Publication of EP3700740A1 publication Critical patent/EP3700740A1/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/0038—Moulds or cores; Details thereof or accessories therefor with sealing means or the like
    • B29C33/0044—Moulds or cores; Details thereof or accessories therefor with sealing means or the like for sealing off parts of inserts projecting into the mould cavity
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5028—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being textile in woven or non-woven form
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between the surfaces to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
    • B29C66/022—Mechanical pre-treatments, e.g. reshaping
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/303—Particular design of joint configurations the joint involving an anchoring effect
    • B29C66/3034—Particular design of joint configurations the joint involving an anchoring effect making use of additional elements, e.g. meshes
    • B29C66/30341—Particular design of joint configurations the joint involving an anchoring effect making use of additional elements, e.g. meshes non-integral with the parts to be joined, e.g. making use of extra elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/52—Joining tubular articles, bars or profiled elements
    • B29C66/524—Joining profiled elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
    • B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/61—Joining from or joining on the inside
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/4835—Heat curing adhesives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5014—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being fibre-reinforced
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3097—Cosmonautical vehicles; Rockets

Definitions

  • the present invention relates to a structural bonding method of structural parts of which at least a first structural part is a composite material part and a second structural part is a composite material part or a metal part, each piece of structure of material composite consisting of a reinforcing preform based on fibers impregnated with a matrix based on polymers, the two structural parts being assembled together during a bonding operation in which an adhesive seal is deposited in a zone defined junction of at least one of said structural parts, said structural parts are pressed against each other and held in position until hardened said glue joint to obtain a rigid structural assembly.
  • the invention also relates to a textured surface insert for implementing said method of structural bonding, a tool for manufacturing a structural part made of composite material comprising at least one mold and a counter mold defining the three-dimensional footprint of said piece of composite material structure to be manufactured, and allowing the shaping of a fiber-reinforced reinforcement preform, the impregnation of the preform with a matrix based on polymers, then the hardening of the part thus obtained, an assembly of at least two structural parts obtained according to said bonding method, and a use of said assembly obtained.
  • the parts to be assembled can be made of identical or different materials.
  • the present invention is more particularly concerned on the one hand with an assembly by bonding two pieces of composite material, and secondly to a bonding assembly of a composite material part and a metal part. Indeed, a bonding assembly of two metal parts is of little interest compared to other existing assembly techniques, such as welding or the like.
  • a car seat is manufactured from a sandwich panel consisting of a sheet of composite material superimposed on a metal sheet by an adhesive intermediate layer consisting of a nonwoven impregnated with a thermosetting resin. It is specified that the metal foil can undergo a plasma treatment to increase the adhesion.
  • the publication WO 03/039851 A1 describes an assembly process by gluing for aircraft of an outer skin made of metal or of composite material on a structural part by means of a pre-cut glue joint and disposed in the zones of junction.
  • This glue joint consists of a layer of glass fibers impregnated with polymerized resin sandwiched between two layers of binder, one polymerized and the other partially polymerized to adjust the thickness of said glue joint by variation. pressure during assembly.
  • the publication EP 2 944 456 A1 relates to a method of repairing a composite material part, such as the outer surface of an aircraft wing, by bonding a repair patch made of the same composite material as the part. to be repaired by means of a bonding interface consisting of a thermosetting adhesive layer sandwiched between two sheets of fabric reinforcement.
  • the publication FR 2 960 881 B1 proposes a reinforced structural bonding method of two pieces made of composite material, in which the adhesive seal is loaded with so-called solid particles. Under the action of a strong pressure on the glue joint, the solid particles penetrate partially into the composite parts to obtain additional mechanical anchoring in their junction zone.
  • the publication US 2016/0265570 A1 proposes to etch the resin on the surface of a composite material part by a laser beam in order to expose the carbon or glass fibers of said part to an adhesive material.
  • This same publication proposes to machine with a laser beam the surface of a metal part to make grooves.
  • the combination of these two surface treatments by removal of material makes it possible to improve the mechanical anchoring of the parts to be assembled.
  • this bonding process is slow to implement, requires immobilization of the parts, and ensures only a mechanical surface anchoring of 0.1 to 0.2 mm which may be insufficient in terms of mechanical strength.
  • the present invention aims to overcome these disadvantages by proposing an industrializable bonding process between two structural parts to produce a composite / composite or composite / metal assembly by means of a conventional glue joint, allowing further improve the mechanical strength in the bonded junction zone, by greatly increasing the specific surface area of the structural parts in their junction zones to create an interpenetration of the materials in the presence, also making it possible to control the thickness of the glue joint added, in particular in a composite / metal assembly, while reducing the surface preparation times of the structural parts to be assembled, which makes it possible to adapt said method to an assembly line, this method being moreover compatible with a large part of the manufacturing processes current composite structural parts and may be suitable for assemblies small and large dimensions and / or simple and complex shapes.
  • the invention relates to a method of the kind indicated in the preamble, characterized in that, prior to the bonding operation, a surface texturing of the junction zone of the two composite material structural parts is performed in a composite / composite assembly or at least the composite structure part in a composite / metal assembly by adding material to increase the specific surface area of said structural parts in their junction zone, in that, to perform said texturing of surface, we add fibers in said junction zone of each structural component part made of composite material which will not be or only partially impregnated during the manufacture of said composite part, and in that, during the gluing operation, when said structural parts are pressed against each other, said textured junction zones interpenetrate and intimately bond each other with said glue joint to increase their mechanical anchorage.
  • a textured surface insert based on textile fibers is manufactured whose shape and dimensions are adapted to those of said zone of junction, and integrates said textured surface insert in each composite material structure part during its manufacture in a tool adapted by orienting said textured surface insert outside said composite material structure part, in said area of joining, and isolating the textile fibers of said textured surface insert to remain dry, to give a specific texture to said junction area and to be exposed to said glue joint during the operation of bonding.
  • said textured surface insert it is possible to produce a complex comprising a first sheet of textile fibers superimposed on a barrier film, said first sheet of textile fibers constituting an outer face of said textured surface insert arranged for being oriented outside said composite material structure part, to remain dry and to give texture to said junction area, and said barrier film being arranged to isolate the outer face of said textured surface insert from said part structure of composite material and to prevent the impregnation of said first sheet of textile fibers by the matrix of said composite material for said textile fibers to remain dry.
  • said barrier film is advantageously dimensioned so that it has a surface greater than the surface of said first textile fiber web in order to create a peripheral rim all around said textured surface insert, this peripheral rim being arranged to cooperate with a seal provided on said adapted tooling.
  • said textured surface insert can be assembled to the reinforcing preform of said composite material by a sewing, needling or tufting technique.
  • said second sheet of textile fibers is advantageously dimensioned so that it has a surface at least equal to the surface of said barrier film.
  • said barrier film is produced in thermoplastic or thermoset sand materials, and said barrier film is intimately joined to said first sheet of textile fibers and / or said second sheet of textile fibers by a heat-bonding, polymerization or cross-linking process. under pressure, to cause interpenetration of said barrier film in said webs of textile fibers binding the components together after curing said barrier film, but without completely impregnating said webs of textile fibers.
  • said first web of textile fibers and / or said second web of textile fibers is produced in two-dimensional webs. obtained from a woven fabric or a nonwoven web, and / or in three-dimensional webs obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, scraped fabric, or a combination of these tablecloths.
  • the three-dimensional plies can be produced from a pile whose pile tufts are oriented predominantly orthogonal to the plane of said ply so as to increase the specific surface area of said structural parts in their junction zone and / or or anchoring said insert in said structural parts of composite material.
  • a composite / metal assembly it is also possible to perform a surface texturing of the junction area of said structural piece of metal material by producing a three-dimensional relief by adding deposited material according to a three-dimensional printing process.
  • the surface texturing of the junction areas of said structural parts to be assembled can be performed by choosing compatible or complementary texturing patterns.
  • the invention also relates to a textured surface insert for implementing the structural bonding method defined above, characterized in that it comprises a complex provided with a first layer of textile fibers superimposed on a barrier film, said first web of textile fibers constituting an outer face of said textured surface insert and being arranged to be oriented outside of said composite material structure part, to remain dry and to give the texture to the junction zone of each piece of composite material structure, and said barrier film being arranged to isolate said first sheet of textile fibers and to prevent its impregnation by the matrix of said composite material to remain dry.
  • said barrier film has a surface greater than the surface of said first web of textile fibers to create a peripheral rim all around said textured surface insert.
  • said textured surface insert may further comprise a second layer of textile fibers superimposed on said barrier film opposite said first sheet of textile fibers, said second sheet of textile fibers constituting an inner face of said textile insert. textured surface and being arranged to be oriented within said composite material structure part, to be impregnated by the matrix of said composite material and to intimately bond said textured surface insert to said composite material part.
  • said second web of textile fibers preferably has a surface at least equal to the surface of said barrier film.
  • the object of the invention is also achieved by a tool as defined in the preamble, characterized in that it is adapted for the implementation of the bonding method defined above, and in that it comprises in said mold at least one recess whose shape and dimensions correspond to those of said determined junction zone and whose depth corresponds to the thickness of said textured surface insert, and a peripheral groove disposed around said recess for receiving a seal for cooperating with the peripheral rim of said textured surface insert to isolate its outer face and prevent the impregnation of said first sheet of textile fibers by the matrix of said composite material injected into said tool so that the textile fibers of said first sheet remain dry during the manufacture of said structural part composite material and give a specific texture to said junction area.
  • the invention relates to an assembly of structural parts obtained by the structural bonding method defined above, and a use of such an assembly as a subassembly or structural assembly for aeronautics, the aerospace, transportation, construction and energy.
  • FIG. 1 is a perspective view of a textured surface insert for implementing the bonding method according to the invention
  • FIG. 2 is a sectional view along the AA section plane of the textured surface insert of FIG. 1,
  • FIG. 3 is a sectional view of a tool for manufacturing a composite part in which the textured surface insert of FIG. 1 has been positioned before the introduction of the preform to produce said composite part,
  • FIG. 4 is a perspective view of a metal part provided in its junction regions with a pattern of reliefs obtained by surface treatment in accordance with the method of the invention
  • FIGS. 5A and 5B are other examples of patterns obtained by surface treatment of the metal part of FIG. 4,
  • FIG. 6 is a perspective view of a structural subassembly obtained by bonding a composite part and a metal part according to the method of the invention
  • Figures 7 and 8 are enlarged views of details VII and Vin of Figure 6
  • Figure 9 is an enlarged sectional view of the composite / metal assembly of Figure 8, and
  • Figure 10 is an enlarged sectional view of a composite / composite assembly.
  • the method of structural bonding of structural parts 1, 2 according to the invention can be applied on the one hand to an assembly between two parts made of composite material, the composite materials in the presence which may be identical or different, and on the other hand to an assembly between a composite material part and a metal part.
  • composite material part must be understood to mean any type of composite parts that can be manufactured and that generally comprise a reinforcing preform based on fibers impregnated with a matrix based on polymers, fibers which may be carbon, glass or any other type commonly used in composite materials, and polymers which may be thermoplastic or thermoset sands resins commonly used in composite materials.
  • a bonding operation consists of depositing an adhesive joint 5 in a junction zone 3, 4 determined from at least one of the parts 1, 2 to be assembled, to press the parts 1, 2 against each other and hold them in position until hardening of the glue joint 5 to obtain a rigid structural assembly.
  • junction zone and “glue joint” used in this application may also be used in the plural.
  • the method according to the invention is distinguished in that, prior to the bonding operation, a surface texturing of the junction zone 3, 4 of each of the pieces 1, 2 is carried out by adding material for the purpose. to increase the specific surface area of the structural parts 1, 2 in their junction zone 3, 4.
  • texturing covers any action aimed at creating a drawing, a pattern, a figure or the like, two-dimensional or three-dimensional, or a combination of the two, the technical effect of which is the increase of the specific surface area of the structural parts 1, 2 in their junction zone 3, 4.
  • This phenomenon necessarily generates a significant increase in the mechanical anchoring of the parts between they allow to reach a high level of mechanical performance that can reach, for example, a gain of at least 50% in resistance to shear stresses compared to a conventional bonding, and depending on the choice chosen to perform the surface texturing.
  • a textured surface insert 6 based on textile fibers is manufactured whose shape and dimensions are adapted to those of each junction zone 3, this textured surface insert 6 is integrated with the structural part 1 made of material composite during its manufacture, by orienting textured surface insert 6 outside of said workpiece 1, isolating the fibers of said textured surface insert 6 to remain dry and thereby provide a texture specific to the junction zone 3 for increasing its specific surface area.
  • FIGS. 1-10 A first example of a textured surface insert 6 is shown in detail in FIGS.
  • first ply 7 of textile fibers constitutes an outer face the textured surface insert 6, arranged to be oriented outside the structural part 1 of composite material, remain dry and give the texture to said junction zone 3.
  • the second ply 9 of textile fibers constitutes a face inside of the textured surface insert 6, arranged to be oriented inside the structural part 1 made of composite material, impregnated by the matrix of said composite material and intimately bonded to said insert
  • the function of the barrier film 8 is to isolate the first ply 7 from the second ply 9 in order to prevent impregnation of the first ply 7 with the matrix of said composite material and to keep dry fibers.
  • the first ply 7 of textile fibers and the second ply 9 of textile fibers may be of construction and of identical or different nature, and may be made in two or three dimensions depending on the desired mechanical performance.
  • the sheets are two-dimensional, they can be obtained from a woven fabric, a nonwoven web, without these examples being limiting.
  • they when they are three-dimensional, they can be obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, a scraped fabric, or a combination of these layers, without these examples being limiting.
  • the fibers protrude transversely to the surface of the ply and form either bristles 7 ', 9' or loops.
  • the tufts of bristles are oriented mainly orthogonally with respect to the plane of the sheet and contribute more to the increase of the specific surface of the junction zones and / or the anchoring of the insert in structural parts made of composite material.
  • any interleaving method of textile fibers may be suitable.
  • any type of design or interlacing pattern of the fibers may be suitable, such as a chevron weave, a jersey knit, a striped or checkered velvet, or the like for the simple purpose of creating an anchor on more efficient possible.
  • the fibers that make up the first and second plies 7 and 9 may be chosen from natural, synthetic, artificial, inorganic textile fibers, such as, for example, aramid, carbon fiber, glass or flax fibers. and any other fiber having in particular a high tensile strength.
  • the barrier film 8 can be made in any type of thermoplastic or thermoset sand, such as for example an epoxy resin or a polyurethane, without these examples being limiting. It should preferably have a glass transition temperature (Tg) greater than the melting temperature of the matrix to preserve its integrity and barrier function at least during manufacture of the composite part. For example, a difference between +10 and + 20 ° C may suffice. This choice remains in the domain of the person skilled in the art.
  • Tg glass transition temperature
  • the barrier film 8 protrudes from this first ply 7 to form a periphery flange 10 on this outer face.
  • the thickness E8 of the barrier film 8 the more the textured surface insert 6 will remain discrete on the surface of the composite structure part 1 and have no influence on the technical characteristics. of the structural part 1 of composite material.
  • the thicknesses of the three components may be between 0.05 and 0.5 mm for the barrier film 8 and between 0.1 and 1 mm for the plies 7 and 9, without these examples being limiting.
  • the three components of the textured surface insert 6, namely the first ply 7, the barrier film 8 and the second ply 9, are joined together intimately by any compatible method, such as a mechanical method by sewing, stapling, or the like, a thermal process by heat sealing, polymerization, crosslinking or the like, or a combination of both.
  • a thermal process will be favored to cause the material of the barrier film 8 to flow towards the plies 7 and 8 (such as schematically illustrated in Figure 2), and thus the interpenetration of the barrier film 8 in each of the layers 7 and 9, binding the components together after curing the barrier film 8.
  • the conditions of this thermal process in terms of temperature, pressure and time are determined by the skilled person according to the nature of the barrier film 8 and are part of his knowledge.
  • the viscosity of the barrier film 8 is important. Viscosity too low would cause capillary effects that would completely impregnate the two layers 7 and 9. It must be high enough to avoid this capillary phenomenon, and for example greater than 10OPa.s without this example being limiting. It depends at the same time on the nature of the barrier film 8 and the temperature of implementation, and the values indicated are not limiting.
  • textured surface insert 6 which has just been described is not limiting, but has the advantage of being easy to industrialize because it can be prepared in advance and outside the production line of parts of structure 1 in composite material. Similarly, it can be easily integrated into the structural part 1 during its manufacture. However, it requires slightly modifying the manufacturing tooling of these parts with reference to FIG. 3.
  • Another variant of embodiment that is not illustrated consists in producing a textured surface insert without the second sheet 9 of textile fibers and in directly bonding it to the reinforcing preform of the future structural part 1 made of composite material.
  • This textured surface insert would comprise only the barrier film and the first ply of textile fibers and would be assembled to said reinforcing preform by any suitable assembly method, such as stitching, needling, tufting, or the like, traversing all or part of the thickness of the reinforcing preform, or by a thermal process as textured surface insert 6 described above.
  • the first web of textile fibers may or may not be completed by reinforcement threads used for needling or tufting. This method of construction can provide extreme mechanical performance, but increases considerably the time of realization. It may, however, have an interest in structural parts with high added value for demanding areas such as aerospace or aeronautics.
  • a tooling 20 allowing the manufacture of a piece 1 of composite material must be slightly modified to be able to integrate textured surface insert 6 in said piece 1 during its manufacture so that it is an integral part of this piece and can not get away from it.
  • a tooling 20 generally comprises at least one rigid mold 21 and a flexible or rigid counter mold 22 (symbolized by an arrow) defining the three-dimensional impression of the component 1 made of composite material to be manufactured, and allowing the forming a reinforcing preform 11 based on fibers, impregnating the preform 11 with a matrix based on polymers, and then hardening the part 1 thus obtained.
  • the bottom of the mold 21 is machined to create a recess 23 whose shape and dimensions correspond to those of the junction zone 3 determined and whose depth P23 corresponds substantially to the thickness of the textured surface insert 6.
  • a throat 24 device is machined around the recess 23 to receive a seal 25, for example elastomer or the like, or any equivalent sealing system.
  • This seal 25 is arranged to create with the peripheral rim 10 of the textured surface insert 6, when the counter mold 22 is closed under pressure, a peripheral sealing zone for isolating the textile fibers of the first 7.
  • the tooling 20 can thus be adapted without much extra cost to the bonding method according to the invention and makes it possible to easily integrate one or more textured surface inserts 6 in the part 1 to be manufactured, the textured surface insert 6 being not limited in size or surface that can range from a few mm 2 to several m 2 .
  • a piece 1 of composite material is obtained in its strict definition, that is to say a solid piece made of a matrix and of a reinforcing preform 11. Only the outer face of the textured surface insert 6 is not or only partially impregnated by the matrix, leaving the dry fibers of the first sheet 7 appear in the junction zone 3.
  • the metal structure part 2 can be prepared specifically by performing a surface texturizing of one or more junction zones 4 by adding material. It may not undergo a texturing step before gluing. We would still obtain a resistance gain through the texturing of the composite part.
  • an additive manufacturing technique is preferably used, by a three-dimensional printing method of the LMD type (Laser Metal Deposition) or the like. This method makes it possible to add a material that is chemically and physically compatible with the metal constituting the structural part 2 to enable it to adhere intimately to the surface of said part.
  • the added material may preferably be metallic, or in some cases synthetic, depending on the chosen three-dimensional printing method and the part 2 to be textured.
  • FIG. 4 represents an example of a piece of metal structure 2 in the form of an omega section, the end flanges of which comprise two longitudinal and parallel bearing zones forming said junction zones 4.
  • junction areas 4 comprise a surface topography formed by pins 12 in relief, obtained by adding material by means of a three-dimensional printing process, these pins 12 being distributed uniformly.
  • the surface topography can have a variable thickness, between 0.1mm and some millimeters, without these values being limiting.
  • the "pin" pattern illustrated is not limiting and extends to any other pattern, which can be determined according to the mechanical stresses of the junction areas 4.
  • the three-dimensional printing pattern can also be chosen according to the drawing or the pattern of the first ply 7 of textile fibers, so that they are compatible or even complementary in part or in whole to further improve the interpenetration of the two junction areas 3 and 4 during the bonding operation of the parts 1 and
  • Figs. 5A and 5B illustrate two further exemplary patterns, one in the form of S-shaped parallel corrugated ribs 13 and the other in the form of parallel straight ribs 14. These patterns may also be uniformly distributed or not in the junction areas 4 to distribute the best constraints according to the solicitation modes encountered.
  • FIG. 6 shows the advantage of the bonding method according to the invention in a concrete application, between a first piece of structure 1 made of composite material in the form of a skin, and several second pieces of metal structure 2 in the form of stiffeners, common assembly in the field of aeronautics and rail for example.
  • the second pieces of metal structure 2 have been texturized from their junction areas 4 by three-dimensional printing, in accordance with FIG. 4.
  • the assembly of these parts 1 and 2 by gluing consists in depositing an adhesive joint 5 in the junction zone or zones 3 and 4 of one or both pieces 1 and 2, pressing them against each other, keeping them in position until the adhesive seam (s) 5 are hardened.
  • the result obtained is illustrated in FIG. 9 in a very enlarged manner and shows an adhesive joint 5 between the two parts 1 and 2, and the interpenetration of the pins 12 of the zone of textured junction 4 of the metal part 2 in the bristles 7 'of the textured junction zone 3 of the piece 1 made of composite material.
  • the invention achieves the goals set, namely a simple bonding process to industrialize to achieve a high level of mechanical performance, and particularly suitable for composite / composite and composite / metal, thus covering a wide range of market assemblies.
  • the present invention is not limited to the embodiments described but extends to any modification and variation obvious to a person skilled in the art.

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Abstract

The present invention relates to a method for structural bonding between a first structural component made of composite material (1) and a second structural component made of composite material (1) or metal (2), wherein, prior to the bonding operation, the surface of the junction region (3, 4) of the two structural components made of composite material (1) in a composite/composite assembly or at least of the structural component made of composite material (1) in a composite/metal assembly is textured by adding material in order to increase the specific surface area of said structural components (1) in the junction region thereof. Thus, during the bonding operation, when the structural components (1, 2) are pressed together, said junction regions (3, 4) interpenetrate and are connected intimately together with said glued joint in order to enhance the mechanical anchoring of said regions.

Description

PROCEDE DE COLLAGE STRUCTURAL DE PIECES DE STRUCTURE ET INSERT DE SURFACE TEXTURÉE POUR LA MISE EN ŒUVRE DUDIT PROCEDE Domaine technique :  METHOD FOR STRUCTURAL BONDING OF STRUCTURAL PARTS AND TEXTURED SURFACE INSERT FOR THE IMPLEMENTATION OF SAID METHOD Technical field:
La présente invention concerne un procédé de collage structural de pièces de structure dont au moins une première pièce de structure est une pièce en matériau composite et une seconde pièce de structure est une pièce en matériau composite ou une pièce métallique, chaque pièce de structure en matériau composite étant constituées d'une préforme de renfort à base de fibres imprégnées d'une matrice à base de polymères, les deux pièces de structure étant assemblées entre elles lors d'une opération de collage dans laquelle on dépose un joint de colle dans une zone de jonction déterminée d'au moins une desdites pièces de structure, on presse lesdites pièces de structure l'une contre l'autre et on les maintient en position jusqu'au durcissement dudit joint de colle pour obtenir un assemblage structurel rigide. The present invention relates to a structural bonding method of structural parts of which at least a first structural part is a composite material part and a second structural part is a composite material part or a metal part, each piece of structure of material composite consisting of a reinforcing preform based on fibers impregnated with a matrix based on polymers, the two structural parts being assembled together during a bonding operation in which an adhesive seal is deposited in a zone defined junction of at least one of said structural parts, said structural parts are pressed against each other and held in position until hardened said glue joint to obtain a rigid structural assembly.
L'invention concerne également un insert de surface texturée permettant la mise en œuvre dudit procédé de collage structural, un outillage pour la fabrication d'une pièce de structure en matériau composite comportant au moins un moule et un contre moule définissant l'empreinte tridimensionnelle de ladite pièce de structure en matériau composite à fabriquer, et permettant la mise en forme d'une préforme de renfort à base de fibres, l'imprégnation de la préforme avec une matrice à base de polymères, puis le durcissement de la pièce ainsi obtenue, un assemblage d'au moins deux pièces de structure obtenu selon ledit procédé de collage, ainsi qu'une utilisation dudit assemblage obtenu. The invention also relates to a textured surface insert for implementing said method of structural bonding, a tool for manufacturing a structural part made of composite material comprising at least one mold and a counter mold defining the three-dimensional footprint of said piece of composite material structure to be manufactured, and allowing the shaping of a fiber-reinforced reinforcement preform, the impregnation of the preform with a matrix based on polymers, then the hardening of the part thus obtained, an assembly of at least two structural parts obtained according to said bonding method, and a use of said assembly obtained.
Technique antérieure D'une manière générale, l'assemblage de pièces par collage pour créer un ensemble ou un sous-ensemble, que ces pièces soient réalisées dans des matériaux identiques ou différents, génère un rendement mécanique médiocre dans la zone de jonction et résiste mal aux contraintes mécaniques auxquelles il est soumis telles que le pelage, la traction, le cisaillement et/ou le clivage. Ce résultat peut ne pas être dérangeant pour un assemblage non structurel, qui n'a pas besoin d'atteindre de hautes performances mécaniques. A l'inverse, ce résultat est proscrit car dangereux pour un assemblage structurel, qui nécessite un haut niveau de performances mécaniques étant donné que la zone de jonction doit pouvoir supporter et transférer des charges. Dans ce cas, la solution la plus courante consiste à surdimensionner les zones de jonction, donc les pièces, au détriment de l'encombrement et du poids de l'assemblage obtenu. D'autres solutions consistent à combiner le collage avec d'autres procédés d'assemblage tels que par rivetage, ou similaire, qui compliquent, alourdissent et renchérissent l'opération d'assemblage. Pour pouvoir mettre en œuvre ces solutions, il est connu d'ajouter des inserts métalliques dans les pièces composites au droit des zones de jonction, ce qui alourdit davantage les pièces et modifie leur structure pouvant engendrer des amorces de rupture. Prior art In general, the assembly of parts by gluing to create an assembly or a subassembly, whether these parts are made of identical or different materials, generates a poor mechanical efficiency in the junction zone and poorly withstands the constraints mechanical forces to which it is subjected such as peeling, pulling, shearing and / or cleaving. This result may not be inconvenient for a non-structural assembly, which does not need to achieve high mechanical performance. Conversely, this result is proscribed as dangerous for a structural assembly, which requires a high level of mechanical performance since the junction area must be able to support and transfer loads. In this case, the most common solution is to oversize the junction areas, so the parts, to the detriment of the size and weight of the assembly obtained. Other solutions consist in combining the bonding with other assembly methods such as riveting, or the like, which complicate, weigh down and increase the assembly operation. In order to be able to implement these solutions, it is known to add metal inserts in the composite parts to the right of the joining zones, which makes the parts more cumbersome and modifies their structure, which can give rise to breakthroughs.
D'autre part, l'utilisation de pièces structurelles en matériau composite se développe de manière exponentielle dans différents secteurs industriels comme l'aéronautique, l'aérospatiale, le transport terrestre et notamment l'automobile, la construction d'ouvrages d'art, l'industrie navale, l'énergie, etc. En effet, les matériaux composites sont très appréciés pour leur légèreté à rigidité mécanique comparable à l'acier, d'où un important gain en poids qui se traduit généralement par une économie d'énergie substantielle. Il est en effet reconnu que 75% de la consommation d'un véhicule est liée à sa masse. Selon les applications, certains sous-ensembles structurels en matériau composite sont fabriqués d'une seule pièce monobloc pour contourner les problèmes d'assemblage, ce qui complique et renchérit considérablement la conception et la fabrication de ces sous-ensembles. Lorsqu'une fabrication monobloc n'est pas envisageable, toutes ou partie des pièces formant le sous-ensemble structurel sont fabriquées séparément puis assemblées par différents procédés. Les procédés mécaniques tels que le soudage et le rivetage sont aujourd'hui les plus utilisés, mais présentent de nombreux inconvénients. Dans le cas de grandes longueurs à assembler, le rivetage impose la mise en place de centaines voire de milliers de rivets, ce qui nécessite un temps de réalisation excessivement long, et génère un surpoids important qui pénalise l'avantage des matières composites. De plus, le perçage des pièces composites pour mettre en place ces rivets est complexe à gérer car il engendre une concentration des contraintes et une fragilisation des pièces au niveau des perçages réalisés. Le soudage est aujourd'hui une technologie qui apporte de très bonnes performances, mais qui est limité à des matériaux de même nature, ayant une même température de fusion. Cette technologie n'est pas adaptée aux assemblages multi-matériaux. Elle ne peut pas non plus être utilisée avec des composites à matrice thermodurcissable qui ne présente pas de point de fusion. Une des solutions permettant de contourner ces inconvénients réside dans des procédés d'assemblage par collage au moyen de matières adhésives adéquates à base de résine époxy, de polyuréthane, d'acrylique ou de toute autre matière adhésive communément utilisée pour ce type d'application. Pour favoriser l'adhésion de la colle sur les pièces composites à assembler, il est nécessaire de leur faire subir un traitement de surface qui peut comporter un sablage de la zone de jonction suivi d'un dégraissage par solvant. On dépose ensuite un film d'une matière adhésive sur au moins une des pièces puis on presse les pièces l'une contre l'autre afin de maintenir les pièces en position pendant la polymérisation ou le durcissement du joint de colle. On cherche ainsi à améliorer l'ancrage mécanique des pièces assemblées par collage. Toutefois, il est avéré que ces opérations de préparation de surface sont très insuffisantes et ne permettent pas d'atteindre un haut niveau de performances mécaniques d'une zone de jonction collée. On the other hand, the use of structural parts in composite material is growing exponentially in various industrial sectors such as aeronautics, aerospace, land transport and especially the automobile, the construction of structures, the shipbuilding industry, energy, etc. Indeed, composite materials are highly appreciated for their lightness with mechanical rigidity comparable to steel, resulting in a significant weight gain that generally results in a substantial energy saving. It is indeed recognized that 75% of the consumption of a vehicle is linked to its mass. Depending on the application, certain structural subassemblies of composite material are manufactured in one piece to circumvent the assembly problems, which complicates and considerably increases the design and manufacture of these subassemblies. When a monobloc manufacture is not possible, all or part of the parts forming the subassembly Structural components are manufactured separately and then assembled by different processes. Mechanical processes such as welding and riveting are today the most used, but have many disadvantages. In the case of long lengths to be assembled, riveting imposes the setting up of hundreds or even thousands of rivets, which requires an excessively long production time, and generates a significant overweight which penalizes the advantage of composite materials. In addition, the drilling of composite parts to set up these rivets is complex to manage because it generates a concentration of constraints and embrittlement of parts at the holes made. Welding is today a technology that provides very good performance, but is limited to materials of the same nature, having the same melting temperature. This technology is not suitable for multi-material assemblies. It can not be used with thermosetting matrix composites that do not have a melting point. One of the solutions to overcome these disadvantages lies in adhesive bonding methods using adequate adhesives based on epoxy resin, polyurethane, acrylic or any other adhesive material commonly used for this type of application. To promote adhesion of the adhesive on the composite parts to be assembled, it is necessary to subject them to a surface treatment which may include sanding of the junction zone followed by degreasing by solvent. A film of an adhesive material is then deposited on at least one of the pieces and the pieces are then pressed against each other to hold the pieces in position during polymerization or curing of the glue joint. It is thus sought to improve the mechanical anchoring of assembled parts by gluing. However, it is proven that these surface preparation operations are very insufficient and do not achieve a high level of mechanical performance of a bonded junction area.
Par ailleurs, selon la conception des sous-ensembles structurels, les pièces à assembler peuvent être réalisées dans des matériaux identiques ou différents. La présente invention s'intéresse plus particulièrement d'une part à un assemblage par collage de deux pièces en matériau composite, et d'autre part à un assemblage par collage d'une pièce en matériau composite et d'une pièce métallique. En effet, un assemblage par collage de deux pièces métalliques ne présente que peu d'intérêt au regard des autres techniques d'assemblage existantes, telles que le soudage ou similaire. Furthermore, according to the design of the structural subassemblies, the parts to be assembled can be made of identical or different materials. The present invention is more particularly concerned on the one hand with an assembly by bonding two pieces of composite material, and secondly to a bonding assembly of a composite material part and a metal part. Indeed, a bonding assembly of two metal parts is of little interest compared to other existing assembly techniques, such as welding or the like.
Certaines solutions se concentrent sur la composition du joint de colle en tant que tel pour améliorer l'adhésion entre pièces, comme dans les publications suivantes. Dans la publication JP 2014/136383 A, on fabrique un siège automobile à partir d'un panneau sandwich constitué d'une feuille en matériau composite superposée à une feuille métallique par une couche intermédiaire adhésive constituée d'un non-tissé imprégné d'une résine thermodurcissable. Il est précisé que la feuille métallique peut subir un traitement plasma pour augmenter l'adhérence. Some solutions focus on the composition of the glue joint as such to improve inter-part adhesion, as in the following publications. In the publication JP 2014/136383 A, a car seat is manufactured from a sandwich panel consisting of a sheet of composite material superimposed on a metal sheet by an adhesive intermediate layer consisting of a nonwoven impregnated with a thermosetting resin. It is specified that the metal foil can undergo a plasma treatment to increase the adhesion.
La publication WO 03/039851 Al décrit un procédé d'assemblage par collage pour aéronefs d'une peau extérieure en métal ou en matériau composite sur une pièce de structure au moyen d'un joint de colle pré-coupé et disposé dans les zones de jonction. Ce joint de colle est constitué d'une couche de fibres de verre imprégnées de résine polymérisée prise en sandwich entre deux couches de liant, l'une polymérisée et l'autre polymérisée partiellement permettant d'ajuster l'épaisseur dudit joint de colle par variation de pression lors de l'assemblage. The publication WO 03/039851 A1 describes an assembly process by gluing for aircraft of an outer skin made of metal or of composite material on a structural part by means of a pre-cut glue joint and disposed in the zones of junction. This glue joint consists of a layer of glass fibers impregnated with polymerized resin sandwiched between two layers of binder, one polymerized and the other partially polymerized to adjust the thickness of said glue joint by variation. pressure during assembly.
La publication EP 2 944 456 Al concerne un procédé de réparation d'une pièce en matériau composite, telle que la surface externe d'une aile d'avion, par collage d'un patch de réparation réalisé dans la même matière composite que la pièce à réparer au moyen d'une interface de liaison constituée d'une couche adhésive thermodurcissable prise en sandwich entre deux feuilles de renfort en tissu. La publication FR 2 960 881 Bl propose un procédé de collage structural renforcé de deux pièces en matériau composite, dans lequel le joint de colle est chargé en particules dites solides. Sous l'action d'une forte pression sur le joint de colle, les particules solides pénètrent en partie dans les pièces composites permettant d'obtenir un ancrage mécanique supplémentaire dans leur zone de jonction. The publication EP 2 944 456 A1 relates to a method of repairing a composite material part, such as the outer surface of an aircraft wing, by bonding a repair patch made of the same composite material as the part. to be repaired by means of a bonding interface consisting of a thermosetting adhesive layer sandwiched between two sheets of fabric reinforcement. The publication FR 2 960 881 B1 proposes a reinforced structural bonding method of two pieces made of composite material, in which the adhesive seal is loaded with so-called solid particles. Under the action of a strong pressure on the glue joint, the solid particles penetrate partially into the composite parts to obtain additional mechanical anchoring in their junction zone.
Toutes ces solutions permettent de calibrer l'épaisseur du joint de colle mais n'assurent pas un ancrage mécanique suffisant pour augmenter drastiquement les performances de la zone de jonction. All these solutions make it possible to calibrate the thickness of the glue joint but do not provide sufficient mechanical anchoring to drastically increase the performance of the junction zone.
D'autres solutions se concentrent sur l'état de surface des pièces à assembler, comme dans les publications suivantes. Other solutions focus on the surface condition of the parts to be assembled, as in the following publications.
La publication US 2016/0265570 Al propose de décaper par un faisceau laser la résine en surface d'une pièce en matériau composite pour exposer les fibres de carbone ou de verre de ladite pièce à une matière adhésive. Cette même publication propose d'usiner par un faisceau laser la surface d'une pièce métallique pour y réaliser des rainures. La combinaison de ces deux traitements de surface par enlèvement de matière permet d'améliorer l'ancrage mécanique des pièces à assembler. Toutefois, ce procédé de collage est long à mettre en œuvre, nécessite une immobilisation des pièces, et n'assure qu'un ancrage mécanique superficiel de 0,1 à 0,2mm qui peut s'avérer insuffisant en termes de résistance mécanique. The publication US 2016/0265570 A1 proposes to etch the resin on the surface of a composite material part by a laser beam in order to expose the carbon or glass fibers of said part to an adhesive material. This same publication proposes to machine with a laser beam the surface of a metal part to make grooves. The combination of these two surface treatments by removal of material makes it possible to improve the mechanical anchoring of the parts to be assembled. However, this bonding process is slow to implement, requires immobilization of the parts, and ensures only a mechanical surface anchoring of 0.1 to 0.2 mm which may be insufficient in terms of mechanical strength.
La publication « New sandwich skin helps panels to outperform conventional counterparts by up to 71% » paru dans le numéro 110, page 26 et 27, de JEC COMPOSITES MAGAZINE de Janvier-Février 2017 propose une technologie par arrachage de matière à la surface de pièces métalliques pour créer des crochets en relief visant à améliorer l'ancrage mécanique au sein d'une structure sandwich constituée de deux plaques en aluminium assemblées entre elles par un noyau en polyéthylène haute densité, pour former un panneau de revêtement de façade. Cette solution est limitée aux pièces métalliques et fragilise les pièces du fait de l'arrachement de matière. Elle est limitée à des surfaces planes, de grandes dimensions, car il semble difficile d'effectuer cette agression mécanique localement. Ainsi, les solutions actuelles cherchant à améliorer l'ancrage mécanique d'un assemblage par collage ne donnent pas entière satisfaction. The publication "New sandwich skin helps panels to outperform", published in issue 110, page 26 and 27, of JEC COMPOSITES MAGAZINE of January-February 2017, proposes a technology by tearing material from the surface of parts metal plates for creating embossed hooks to improve mechanical anchoring within a sandwich structure of two aluminum plates joined together by a high density polyethylene core to form a facade cladding panel. This solution is limited to metal parts and weakens parts due to tearing material. It is limited to large flat surfaces because it seems difficult to carry out this mechanical attack locally. Thus, current solutions seeking to improve the mechanical anchoring of an assembly by gluing are not entirely satisfactory.
Exposé de l'invention : La présente invention vise à pallier ces inconvénients en proposant un procédé de collage industrialisable entre deux pièces de structure pour réaliser un assemblage composite/composite ou composite/métallique au moyen d'un joint de colle classique, permettant d'améliorer davantage la tenue mécanique dans la zone de jonction collée, en augmentant largement la surface spécifique des pièces de structure dans leurs zones de jonction pour créer une interpénétration des matériaux en présence, permettant également de maîtriser l'épaisseur du joint de colle ajouté notamment dans un assemblage composite/métallique, tout en réduisant les temps de préparation de surface des pièces de structure à assembler, ce qui permet d'adapter ledit procédé à une chaîne de montage, ce procédé étant en outre compatible avec une grande partie des procédés de fabrication actuels des pièces de structure composites et pouvant convenir à des assemblages de petites et de grandes dimensions et/ou de formes simples et complexes. SUMMARY OF THE INVENTION The present invention aims to overcome these disadvantages by proposing an industrializable bonding process between two structural parts to produce a composite / composite or composite / metal assembly by means of a conventional glue joint, allowing further improve the mechanical strength in the bonded junction zone, by greatly increasing the specific surface area of the structural parts in their junction zones to create an interpenetration of the materials in the presence, also making it possible to control the thickness of the glue joint added, in particular in a composite / metal assembly, while reducing the surface preparation times of the structural parts to be assembled, which makes it possible to adapt said method to an assembly line, this method being moreover compatible with a large part of the manufacturing processes current composite structural parts and may be suitable for assemblies small and large dimensions and / or simple and complex shapes.
Dans ce but, l'invention concerne un procédé du genre indiqué en préambule, caractérisé en ce que, préalablement à l'opération de collage, on effectue une texturation de surface de la zone de jonction des deux pièces de structure en matériau composite dans un assemblage composite/composite ou d'au moins la pièce de structure en matériau composite dans un assemblage composite/métallique par ajout de matière pour augmenter la surface spécifique desdites pièces de structure dans leur zone de jonction, en ce que, pour effectuer ladite texturation de surface, on ajoute des fibres dans ladite zone de jonction de chaque pièce de structure en matériau composite qui ne seront pas ou que partiellement imprégnées pendant la fabrication de ladite pièce composite, et en ce que, lors de l'opération de collage, lorsque lesdites pièces de structure sont pressées l'une contre l'autre, lesdites zones de jonction texturées s'interpénétrent et se lient intimement entre-elles avec ledit joint de colle pour augmenter leur ancrage mécanique. For this purpose, the invention relates to a method of the kind indicated in the preamble, characterized in that, prior to the bonding operation, a surface texturing of the junction zone of the two composite material structural parts is performed in a composite / composite assembly or at least the composite structure part in a composite / metal assembly by adding material to increase the specific surface area of said structural parts in their junction zone, in that, to perform said texturing of surface, we add fibers in said junction zone of each structural component part made of composite material which will not be or only partially impregnated during the manufacture of said composite part, and in that, during the gluing operation, when said structural parts are pressed against each other, said textured junction zones interpenetrate and intimately bond each other with said glue joint to increase their mechanical anchorage.
De manière avantageuse, pour effectuer ladite texturation de surface de la zone de jonction de chaque pièce de structure en matériau composite, on fabrique un insert de surface texturée à base de fibres textiles dont la forme et les dimensions sont adaptées à celles de ladite zone de jonction, et on intègre ledit insert de surface texturée dans chaque pièce de structure en matériau composite lors de sa fabrication dans un outillage adapté en orientant ledit insert de surface texturée à l'extérieur de ladite pièce de structure en matériau composite, dans ladite zone de jonction, et en isolant les fibres textiles dudit insert de surface texturée pour qu'elles restent sèches, pour qu'elles donnent une texture spécifique à ladite zone de jonction et pour qu'elles soient exposées audit joint de colle lors de l'opération de collage. Advantageously, in order to perform said surface texturing of the junction zone of each piece of composite material structure, a textured surface insert based on textile fibers is manufactured whose shape and dimensions are adapted to those of said zone of junction, and integrates said textured surface insert in each composite material structure part during its manufacture in a tool adapted by orienting said textured surface insert outside said composite material structure part, in said area of joining, and isolating the textile fibers of said textured surface insert to remain dry, to give a specific texture to said junction area and to be exposed to said glue joint during the operation of bonding.
Pour fabriquer ledit insert de surface texturée, et selon les variantes de réalisation, on peut réaliser un complexe comportant une première nappe de fibres textiles superposée à un film barrière, ladite première nappe de fibres textiles constituant une face extérieure dudit insert de surface texturée agencée pour être orientée à l'extérieur de ladite pièce de structure en matériau composite, pour rester sèche et pour donner la texture à ladite zone de jonction, et ledit film barrière étant agencé pour isoler la face extérieure dudit insert de surface texturée par rapport à ladite pièce de structure en matériau composite et pour empêcher l'imprégnation de ladite première nappe de fibres textiles par la matrice dudit matériau composite pour que lesdites fibres textiles restent sèches. Dans ce cas, on dimensionne avantageusement ledit film barrière pour qu'il ait une surface supérieure à la surface de ladite première nappe de fibres textiles afin de créer un rebord périphérique tout autour dudit insert de surface texturée, ce rebord périphérique étant agencé pour coopérer avec un joint d'étanchéité prévu sur ledit outillage adapté. To manufacture said textured surface insert, and according to the embodiments, it is possible to produce a complex comprising a first sheet of textile fibers superimposed on a barrier film, said first sheet of textile fibers constituting an outer face of said textured surface insert arranged for being oriented outside said composite material structure part, to remain dry and to give texture to said junction area, and said barrier film being arranged to isolate the outer face of said textured surface insert from said part structure of composite material and to prevent the impregnation of said first sheet of textile fibers by the matrix of said composite material for said textile fibers to remain dry. In this case, said barrier film is advantageously dimensioned so that it has a surface greater than the surface of said first textile fiber web in order to create a peripheral rim all around said textured surface insert, this peripheral rim being arranged to cooperate with a seal provided on said adapted tooling.
Dans un premier mode de réalisation, on peut assembler ledit insert de surface texturée à la préforme de renfort dudit matériau composite par une technique de couture, d'aiguilletage ou de touffetage. In a first embodiment, said textured surface insert can be assembled to the reinforcing preform of said composite material by a sewing, needling or tufting technique.
Dans un second mode de réalisation, on peut ajouter au complexe formant ledit insert de surface texturée une seconde nappe de fibres textiles superposée audit film barrière à l'opposé de ladite première nappe de fibres textiles, ladite seconde nappe de fibres textiles constituant une face intérieure dudit insert de surface texturée agencée pour être orientée à l'intérieur de ladite pièce de structure en matériau composite et pour être imprégnée par la matrice dudit matériau composite. In a second embodiment, one may add to the complex forming said textured surface insert a second web of textile fibers superimposed on said barrier film opposite said first web of textile fibers, said second web of textile fibers constituting an inner face said textured surface insert arranged to be oriented within said composite material structural part and to be impregnated by the matrix of said composite material.
Dans ce cas, on dimensionne avantageusement ladite seconde nappe de fibres textiles pour qu'elle ait une surface au moins égale à la surface dudit film barrière. In this case, said second sheet of textile fibers is advantageously dimensioned so that it has a surface at least equal to the surface of said barrier film.
De préférence, on réalise ledit film barrière dans des matières thermoplastiques ou thermodurcis sables, et on assemble intimement ledit film barrière à ladite première nappe de fibres textiles et/ou ladite seconde nappe de fibres textiles par un procédé de thermocollage, de polymérisation ou de réticulation, sous pression, pour provoquer l'interpénétration dudit film barrière dans lesdites nappes de fibres textiles liant les composants entre eux après durcissement dudit film barrière, mais sans imprégner totalement lesdites nappes de fibres textiles. Preferably, said barrier film is produced in thermoplastic or thermoset sand materials, and said barrier film is intimately joined to said first sheet of textile fibers and / or said second sheet of textile fibers by a heat-bonding, polymerization or cross-linking process. under pressure, to cause interpenetration of said barrier film in said webs of textile fibers binding the components together after curing said barrier film, but without completely impregnating said webs of textile fibers.
Selon les variantes de réalisation, on réalise ladite première nappe de fibres textiles et/ou ladite seconde nappe de fibres textiles dans des nappes bidimensionnelles obtenues à partir d'un tissu tissé ou d'un voile non tissé, et/ou dans des nappes tridimensionnelles obtenues à partir d'un velours lisse ou côtelé, d'un tricot, d'un non-tissé aiguilleté, d'un tissu touffeté, d'un tissu gratté, ou d'une combinaison de ces nappes. According to the embodiments, said first web of textile fibers and / or said second web of textile fibers is produced in two-dimensional webs. obtained from a woven fabric or a nonwoven web, and / or in three-dimensional webs obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, scraped fabric, or a combination of these tablecloths.
De manière avantageuse, on peut réaliser les nappes tridimensionnelles à partir d'un velours dont les touffes de poils sont orientées majoritairement orthogonalement par rapport au plan de ladite nappe de sorte à augmenter la surface spécifique desdites pièces de structure dans leur zone de jonction et/ou l'ancrage dudit insert dans lesdites pièces de structure en matériau composite. Advantageously, the three-dimensional plies can be produced from a pile whose pile tufts are oriented predominantly orthogonal to the plane of said ply so as to increase the specific surface area of said structural parts in their junction zone and / or or anchoring said insert in said structural parts of composite material.
Dans un assemblage composite/métallique, on peut effectuer également une texturation de surface de la zone de jonction de ladite pièce de structure en matériau métallique en réalisant un relief tridimensionnel par ajout de matière déposée selon un procédé d'impression tridimensionnelle. In a composite / metal assembly, it is also possible to perform a surface texturing of the junction area of said structural piece of metal material by producing a three-dimensional relief by adding deposited material according to a three-dimensional printing process.
Dans ce cas, on choisit ladite matière à déposer parmi les matières synthétiques et métalliques compatibles avec la matière métallique de ladite pièce de structure à assembler. In this case, one chooses said material to be deposited among the synthetic and metallic materials compatible with the metallic material of said structural part to be assembled.
En fonction des buts visés, on peut effectuer la texturation de surface des zones de jonction desdites pièces de structure à assembler en choisissant des motifs de texturation compatibles ou complémentaires. Dans ce but, l'invention concerne également un insert de surface texturée permettant la mise en œuvre du procédé de collage structural défini ci-dessus, caractérisé en ce qu'il comporte un complexe pourvu d'une première nappe de fibres textiles superposée à un film barrière, ladite première nappe de fibres textiles constituant une face extérieure dudit insert de surface texturée et étant agencée pour être orientée à l'extérieur de ladite pièce de structure en matériau composite, pour rester sèche et pour donner la texture à la zone de jonction de chaque pièce de structure en matériau composite, et ledit film barrière étant agencé pour isoler ladite première nappe de fibres textiles et pour empêcher son imprégnation par la matrice dudit matériau composite pour qu'elle reste sèche. Depending on the aims, the surface texturing of the junction areas of said structural parts to be assembled can be performed by choosing compatible or complementary texturing patterns. For this purpose, the invention also relates to a textured surface insert for implementing the structural bonding method defined above, characterized in that it comprises a complex provided with a first layer of textile fibers superimposed on a barrier film, said first web of textile fibers constituting an outer face of said textured surface insert and being arranged to be oriented outside of said composite material structure part, to remain dry and to give the texture to the junction zone of each piece of composite material structure, and said barrier film being arranged to isolate said first sheet of textile fibers and to prevent its impregnation by the matrix of said composite material to remain dry.
Dans une forme de réalisation préférée, ledit film barrière a une surface supérieure à la surface de ladite première nappe de fibres textiles afin de créer un rebord périphérique tout autour dudit insert de surface texturée. Selon les variantes de réalisation, ledit insert de surface texturée peut comporter en outre une seconde nappe de fibres textiles superposée audit film barrière à l'opposé de ladite première nappe de fibres textiles, ladite seconde nappe de fibres textiles constituant une face intérieure dudit insert de surface texturée et étant agencée pour être orientée à l'intérieur de ladite pièce de structure en matériau composite, pour être imprégnée par la matrice dudit matériau composite et pour lier intimement ledit insert de surface texturée à ladite pièce de structure en matériau composite. Dans ce cas, ladite seconde nappe de fibres textiles a de préférence une surface au moins égale à la surface dudit film barrière. Le but de l'invention est également atteint par un outillage tel que défini en préambule, caractérisé en ce qu'il est adapté pour la mise en œuvre du procédé de collage défini ci-dessus, et en ce qu'il comporte dans ledit moule au moins un évidement dont la forme et les dimensions correspondent à celles de ladite zone de jonction déterminée et dont la profondeur correspond à l'épaisseur dudit insert de surface texturée, et une gorge périphérique disposée autour dudit évidement pour recevoir un joint d'étanchéité destiné à coopérer avec le rebord périphérique dudit insert de surface texturée afin d'isoler sa face extérieure et empêcher l'imprégnation de ladite première nappe de fibres textiles par la matrice dudit matériau composite injectée dans ledit outillage pour que les fibres textiles de ladite première nappe restent sèches lors de la fabrication de ladite pièce de structure en matériau composite et donnent une texture spécifique à ladite zone de jonction. In a preferred embodiment, said barrier film has a surface greater than the surface of said first web of textile fibers to create a peripheral rim all around said textured surface insert. According to the variant embodiments, said textured surface insert may further comprise a second layer of textile fibers superimposed on said barrier film opposite said first sheet of textile fibers, said second sheet of textile fibers constituting an inner face of said textile insert. textured surface and being arranged to be oriented within said composite material structure part, to be impregnated by the matrix of said composite material and to intimately bond said textured surface insert to said composite material part. In this case, said second web of textile fibers preferably has a surface at least equal to the surface of said barrier film. The object of the invention is also achieved by a tool as defined in the preamble, characterized in that it is adapted for the implementation of the bonding method defined above, and in that it comprises in said mold at least one recess whose shape and dimensions correspond to those of said determined junction zone and whose depth corresponds to the thickness of said textured surface insert, and a peripheral groove disposed around said recess for receiving a seal for cooperating with the peripheral rim of said textured surface insert to isolate its outer face and prevent the impregnation of said first sheet of textile fibers by the matrix of said composite material injected into said tool so that the textile fibers of said first sheet remain dry during the manufacture of said structural part composite material and give a specific texture to said junction area.
Dans ce but, l'invention concerne un assemblage de pièces de structure obtenu par le procédé de collage structural défini ci-dessus, ainsi qu'une utilisation d'un tel assemblage comme sous-ensemble ou ensemble structurel pour l'aéronautique, l'aérospatiale, le transport, la construction et l'énergie. For this purpose, the invention relates to an assembly of structural parts obtained by the structural bonding method defined above, and a use of such an assembly as a subassembly or structural assembly for aeronautics, the aerospace, transportation, construction and energy.
Description sommaire des dessins : Brief description of the drawings:
La présente invention et ses avantages apparaîtront mieux dans la description suivante d'un mode de réalisation donné à titre d'exemple non limitatif, en référence aux dessins annexés, dans lesquels: The present invention and its advantages will appear better in the following description of an embodiment given by way of non-limiting example, with reference to the appended drawings, in which:
la figure 1 est une vue en perspective d'un insert de surface texturée pour la mise en œuvre du procédé de collage selon l'invention,  FIG. 1 is a perspective view of a textured surface insert for implementing the bonding method according to the invention,
la figure 2 est une vue en coupe selon le plan de coupe AA de l'insert de surface texturée de la figure 1,  FIG. 2 is a sectional view along the AA section plane of the textured surface insert of FIG. 1,
la figure 3 est une vue en coupe d'un outillage pour la fabrication d'une pièce composite dans lequel l'insert de surface texturée de la figure 1 a été positionné avant la mise en place de la préforme pour réaliser ladite pièce composite,  FIG. 3 is a sectional view of a tool for manufacturing a composite part in which the textured surface insert of FIG. 1 has been positioned before the introduction of the preform to produce said composite part,
la figure 4 est une vue en perspective d'une pièce métallique pourvue dans ses zones de jonction d'un motif de reliefs obtenus par traitement de surface conformément au procédé de l'invention,  FIG. 4 is a perspective view of a metal part provided in its junction regions with a pattern of reliefs obtained by surface treatment in accordance with the method of the invention;
les figures 5 A et 5B sont d'autres exemples de motifs obtenus par traitement de surface de la pièce métallique de la figure 4,  FIGS. 5A and 5B are other examples of patterns obtained by surface treatment of the metal part of FIG. 4,
la figure 6 est une vue en perspective d'un sous-ensemble structurel obtenu par collage d'une pièce composite et d'une pièce métallique conformément au procédé de l'invention, les figures 7 et 8 sont des vues agrandies des détails VII et Vin de la figure 6, la figure 9 est une vue en coupe agrandie de l'assemblage composite/métallique de la figure 8, et FIG. 6 is a perspective view of a structural subassembly obtained by bonding a composite part and a metal part according to the method of the invention, Figures 7 and 8 are enlarged views of details VII and Vin of Figure 6, Figure 9 is an enlarged sectional view of the composite / metal assembly of Figure 8, and
la figure 10 est une vue en coupe agrandie d'un assemblage composite/composite.  Figure 10 is an enlarged sectional view of a composite / composite assembly.
Illustrations de l'invention et différentes manières de la réaliser : Illustrations of the invention and different ways of making it:
Dans les exemples de réalisation illustrés, les éléments ou parties identiques portent les mêmes numéros de référence. In the exemplary embodiments illustrated, the elements or identical parts bear the same reference numbers.
En référence aux figures, le procédé de collage structural de pièces de structure 1, 2 selon l'invention peut s'appliquer d'une part à un assemblage entre deux pièces en matériau composite, les matériaux composites en présence pouvant être identiques ou non, et d'autre part à un assemblage entre une pièce en matériau composite et une pièce métallique. Dans le cadre de l'invention, il faut comprendre par « pièce en matériau composite » tout type de pièces composites qu'il est possible de fabriquer et qui comportent généralement une préforme de renfort à base de fibres imprégnées d'une matrice à base de polymères, les fibres pouvant être des fibres de carbone, de verre, ou de toute autre nature communément utilisée dans les matériaux composites, et les polymères pouvant être des résines thermoplastiques ou thermodurcis sables communément utilisées dans les matériaux composites. De même, il faut comprendre par « pièce métallique » tout type de pièces métalliques qu'il est possible de fabriquer à partir d'acier, d'acier inoxydable ou de tout autre alliage métallique communément utilisé pour la fabrication de pièces de structure. Par « pièce de structure », il faut comprendre toute pièce destinée à supporter et à transmettre ou transférer des charges. Bien entendu, l'invention peut s'appliquer à des pièces non structurelles, mais dans ce cas, n'aurait que peu d'intérêt économique. De manière tout à fait classique, une opération de collage consiste à déposer un joint de colle 5 dans une zone de jonction 3, 4 déterminée d'au moins une des pièces 1, 2 à assembler, à presser les pièces 1, 2 l'une contre l'autre et à les maintenir en position jusqu'au durcissement du joint de colle 5 pour obtenir un assemblage structurel rigide. Les termes « zone de jonction » et «joint de colle » utilisés dans la présente demande, peuvent s'entendre également au pluriel. With reference to the figures, the method of structural bonding of structural parts 1, 2 according to the invention can be applied on the one hand to an assembly between two parts made of composite material, the composite materials in the presence which may be identical or different, and on the other hand to an assembly between a composite material part and a metal part. In the context of the invention, the term "composite material part" must be understood to mean any type of composite parts that can be manufactured and that generally comprise a reinforcing preform based on fibers impregnated with a matrix based on polymers, fibers which may be carbon, glass or any other type commonly used in composite materials, and polymers which may be thermoplastic or thermoset sands resins commonly used in composite materials. Similarly, the term "metal part" any type of metal parts that can be made from steel, stainless steel or any other metal alloy commonly used for the manufacture of structural parts. "Structural part" means any part intended to support and transmit or transfer loads. Of course, the invention can be applied to non-structural parts, but in this case would have little economic interest. In a very conventional manner, a bonding operation consists of depositing an adhesive joint 5 in a junction zone 3, 4 determined from at least one of the parts 1, 2 to be assembled, to press the parts 1, 2 against each other and hold them in position until hardening of the glue joint 5 to obtain a rigid structural assembly. The terms "junction zone" and "glue joint" used in this application may also be used in the plural.
Le procédé selon l'invention se singularise en ce que l'on effectue, préalablement à l'opération de collage, une texturation de surface de la zone de jonction 3, 4 de chacune des pièces 1, 2 par ajout de matière dans le but d'augmenter la surface spécifique des pièces de structure 1, 2 dans leur zone de jonction 3, 4. Le terme « texturation » couvre toute action visant à créer un dessin, un motif, une figure ou similaire, bidimensionnel ou tridimensionnel ou encore en une combinaison des deux, dont l'effet technique est l'augmentation de la surface spécifique des pièces de structure 1, 2 dans leur zone de jonction 3, 4. Ainsi, lors de l'opération de collage, les zones de jonction 3, 4 texturées des pièces de structure 1, 2 et pressées l'une contre l'autre s'interpénétrent et se lient intimement entre-elles avec le joint de colle 5. Ce phénomène engendre nécessairement une augmentation importante de l'ancrage mécanique des pièces entre elles permettant d'atteindre un haut niveau de performance mécanique pouvant atteindre par exemple un gain d'au moins 50% de résistance pour des sollicitations en cisaillement par rapport à un collage classique, et en fonction du choix retenu pour effectuer la texturation de surface. The method according to the invention is distinguished in that, prior to the bonding operation, a surface texturing of the junction zone 3, 4 of each of the pieces 1, 2 is carried out by adding material for the purpose. to increase the specific surface area of the structural parts 1, 2 in their junction zone 3, 4. The term "texturing" covers any action aimed at creating a drawing, a pattern, a figure or the like, two-dimensional or three-dimensional, or a combination of the two, the technical effect of which is the increase of the specific surface area of the structural parts 1, 2 in their junction zone 3, 4. Thus, during the bonding operation, the junction zones 3, 4 textured pieces of structure 1, 2 and pressed against each other interpenetrate and intimately bonded to each other with the adhesive joint 5. This phenomenon necessarily generates a significant increase in the mechanical anchoring of the parts between they allow to reach a high level of mechanical performance that can reach, for example, a gain of at least 50% in resistance to shear stresses compared to a conventional bonding, and depending on the choice chosen to perform the surface texturing.
Pour effectuer la texturation de surface de chaque zone de jonction 3 de la pièce de structure 1 en matériau composite ou de chacune des pièces en matériau composite, on ajoute des fibres qui ne seront pas ou que partiellement imprégnées pendant la fabrication de la pièce composite. Dans ce but, on fabrique un insert de surface texturée 6 à base de fibres textiles dont la forme et les dimensions sont adaptées à celles de chaque zone de jonction 3, on intègre cet insert de surface texturée 6 à la pièce de structure 1 en matériau composite lors de sa fabrication, en orientant ledit insert de surface texturée 6 à l'extérieur de ladite pièce 1, en isolant les fibres dudit insert de surface texturée 6 pour qu'elles restent sèches et donnent ainsi une texture spécifique à la zone de jonction 3 visant à augmenter sa surface spécifique. Un premier exemple d' insert de surface texturée 6 est représenté en détail dans les figures 1 et 2 dans lequel il apparaît sous la forme d'un rectangle de surface plane. Cet exemple n'est pas limitatif et s'étend à toute autre forme géométrique ou complexe, de surface plane, courbe ou complexe, définies en fonction de la forme et de la surface des zones de jonction 3 et 4. Il est formé d'un complexe comprenant une première nappe 7 de fibres textiles superposée à un film barrière 8 et une seconde nappe 9 de fibres textiles superposée audit film barrière 8 à l'opposé de ladite première nappe 7. La première nappe 7 de fibres textiles constitue une face extérieure de l'insert de surface texturée 6, agencée pour être orientée à l'extérieur de la pièce de structure 1 en matériau composite, rester sèche et donner la texture à ladite zone de jonction 3. La seconde nappe 9 de fibres textiles constitue une face intérieure de l'insert de surface texturée 6, agencée pour être orientée à l'intérieur de la pièce de structure 1 en matériau composite, imprégnée par la matrice dudit matériau composite et liée intimement ledit insert de surface texturée 6 à ladite pièce de structure 1. Le film barrière 8 a pour fonction d'isoler la première nappe 7 de la seconde nappe 9 afin d'empêcher l'imprégnation de la première nappe 7 par la matrice dudit matériau composite et de conserver des fibres sèches. To effect the surface texturing of each junction zone 3 of the structural part 1 made of composite material or of each of the composite material parts, fibers which will not be or only partially impregnated during the manufacture of the composite part are added. For this purpose, a textured surface insert 6 based on textile fibers is manufactured whose shape and dimensions are adapted to those of each junction zone 3, this textured surface insert 6 is integrated with the structural part 1 made of material composite during its manufacture, by orienting textured surface insert 6 outside of said workpiece 1, isolating the fibers of said textured surface insert 6 to remain dry and thereby provide a texture specific to the junction zone 3 for increasing its specific surface area. A first example of a textured surface insert 6 is shown in detail in FIGS. 1 and 2 in which it appears in the form of a flat surface rectangle. This example is not limiting and extends to any other geometric or complex shape, of flat, curved or complex surface, defined according to the shape and the surface of the junction zones 3 and 4. It is formed of a complex comprising a first ply 7 of textile fibers superimposed on a barrier film 8 and a second ply 9 of textile fibers superimposed on said barrier film 8 opposite said first ply 7. The first ply 7 of textile fibers constitutes an outer face the textured surface insert 6, arranged to be oriented outside the structural part 1 of composite material, remain dry and give the texture to said junction zone 3. The second ply 9 of textile fibers constitutes a face inside of the textured surface insert 6, arranged to be oriented inside the structural part 1 made of composite material, impregnated by the matrix of said composite material and intimately bonded to said insert The function of the barrier film 8 is to isolate the first ply 7 from the second ply 9 in order to prevent impregnation of the first ply 7 with the matrix of said composite material and to keep dry fibers.
La première nappe 7 de fibres textiles et la seconde nappe 9 de fibres textiles peuvent être de construction et de nature identique ou non, et peuvent être réalisées en deux ou en trois dimensions en fonction des performances mécaniques recherchées. Lorsque les nappes sont bidimensionnelles, elles peuvent être obtenues à partir d'un tissu tissé, d'un voile non tissé, sans que ces exemples ne soient limitatifs. Et lorsqu'elles sont tridimensionnelles, elles peuvent être obtenues à partir d'un velours lisse ou côtelé, d'un tricot, d'un non-tissé aiguilleté, d'un tissu touffeté, d'un tissu gratté, ou encore une combinaison de ces nappes, sans que ces exemples ne soient limitatifs. Dans le cas de nappes tridimensionnelles, les fibres dépassent transversalement à la surface de la nappe et forment soit des poils 7', 9' soit des boucles. Dans le cas plus spécifique du velours, les touffes de poils sont orientées majoritairement orthogonalement par rapport au plan de la nappe et contribuent davantage à l'augmentation de la surface spécifique des zones de jonction et/ou de l'ancrage de l'insert dans les pièces de structure en matériau composite. Ces exemples ne sont pas limitatifs et tout procédé d'entrelacement de fibres textiles peut convenir. De même, tout type de dessin ou de motif d'entrelacement des fibres peut convenir, comme par exemple un tissage en chevron, un tricot en jersey, un velours à rayures ou à damier, ou similaire dans le simple but de créer un ancrage le plus efficace possible. Les fibres qui composent les première et seconde nappes 7 et 9 peuvent être choisies parmi les fibres textiles naturelles, synthétiques, artificielles, inorganiques, telles qu'à titre d'exemples des fibres d'aramide, de carbone, de verre, de lin, et toute autre fibre ayant notamment une résistance élevée à la traction. The first ply 7 of textile fibers and the second ply 9 of textile fibers may be of construction and of identical or different nature, and may be made in two or three dimensions depending on the desired mechanical performance. When the sheets are two-dimensional, they can be obtained from a woven fabric, a nonwoven web, without these examples being limiting. And when they are three-dimensional, they can be obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, a scraped fabric, or a combination of these layers, without these examples being limiting. In the case of three-dimensional plies, the fibers protrude transversely to the surface of the ply and form either bristles 7 ', 9' or loops. In the more specific case of velvet, the tufts of bristles are oriented mainly orthogonally with respect to the plane of the sheet and contribute more to the increase of the specific surface of the junction zones and / or the anchoring of the insert in structural parts made of composite material. These examples are not limiting and any interleaving method of textile fibers may be suitable. Similarly, any type of design or interlacing pattern of the fibers may be suitable, such as a chevron weave, a jersey knit, a striped or checkered velvet, or the like for the simple purpose of creating an anchor on more efficient possible. The fibers that make up the first and second plies 7 and 9 may be chosen from natural, synthetic, artificial, inorganic textile fibers, such as, for example, aramid, carbon fiber, glass or flax fibers. and any other fiber having in particular a high tensile strength.
Le film barrière 8 peut être réalisé dans tout type de matières thermoplastiques ou thermodurcis sables, comme par exemple une résine époxy ou un polyuréthane, sans que ces exemples ne soient limitatifs. Il doit avoir de préférence une température de transition vitreuse (Tg) supérieure à la température de fusion de la matrice pour préserver son intégrité et sa fonction barrière au moins pendant la fabrication de la pièce composite. A titre d'exemple, un écart entre +10 et +20°C peut suffire. Ce choix reste du domaine de l'homme du métier. The barrier film 8 can be made in any type of thermoplastic or thermoset sand, such as for example an epoxy resin or a polyurethane, without these examples being limiting. It should preferably have a glass transition temperature (Tg) greater than the melting temperature of the matrix to preserve its integrity and barrier function at least during manufacture of the composite part. For example, a difference between +10 and + 20 ° C may suffice. This choice remains in the domain of the person skilled in the art.
Pour assurer un isolement correct de la première nappe 7 située sur la face extérieure de l'insert de surface texturée 6, il est nécessaire que le film barrière 8 dépasse de cette première nappe 7 pour former un rebord périphérie 10 sur cette face extérieure. Ce rebord périphérique 10 est agencé pour entrer en contact avec un système d'étanchéité prévu spécifiquement sur l'outillage permettant la fabrication de la pièce de structure 1 en matériau composite, comme décrit plus loin en référence à la figure 3. C'est ainsi que pour réaliser l'insert de surface texturée 6, on découpe les première et seconde nappes 7 et 9 et le film barrière 8 de telle sorte que la surface S7 de la première nappe 7 soit inférieure à la surface S8 du film barrière 8 et que la surface S9 de la seconde nappe 9 soit au moins égale à la surface S8 du film barrière 8 : S7 < S8 < ou = S9. Puis on superpose le film barrière 8 sur la seconde nappe 9 et la première nappe 7 sur le film barrière 8 en prenant soin de la centrer pour que le rebord périphérique 10 dépasse tout autour de la première nappe 7. To ensure correct isolation of the first ply 7 located on the outer face of the textured surface insert 6, it is necessary that the barrier film 8 protrudes from this first ply 7 to form a periphery flange 10 on this outer face. This peripheral rim 10 is arranged to come into contact with a sealing system provided specifically on the tooling for manufacturing the structural part 1 made of composite material, as described below with reference to FIG. for producing the textured surface insert 6, the first and second plies 7 and 9 and the barrier film 8 so that the surface S7 of the first ply 7 is smaller than the surface S8 of the barrier film 8 and the surface S9 of the second ply 9 is at least equal to the surface S8 of the barrier film 8: S7 <S8 <or = S9. Then the barrier film 8 is superimposed on the second ply 9 and the first ply 7 on the barrier film 8, taking care to center it so that the peripheral flange 10 projects all around the first ply 7.
Il convient également de respecter une certaine distribution des épaisseurs entre les trois composants. Le film barrière 8 doit présenter de préférence une épaisseur E8 inférieure à l'épaisseur E7 et E9 des nappes 7 et 9 de fibres textiles pour éviter de remplir intégralement les nappes 7 et 9 par fluage au moment de la fabrication de l'insert de surface texturée 6. Elle peut être par exemple égale ou inférieure à la moitié de l'épaisseur des nappes 7 et 9 : E8 < E7 et E9 et de préférence E8 < ou = ½ E7 ou E9. L'épaisseur E7 et E9 des nappes 7 et 9 est mesurée sous pression, idéalement à la pression correspondant à la fabrication de l'insert de surface texturée 6. It is also necessary to respect a certain distribution of the thicknesses between the three components. The barrier film 8 should preferably have a thickness E8 less than the thickness E7 and E9 of the plies 7 and 9 of textile fibers to avoid filling the plies 7 and 9 integrally by creep at the time of manufacture of the surface insert. 6. It may for example be equal to or less than half the thickness of the plies 7 and 9: E8 <E7 and E9 and preferably E8 <or = ½ E7 or E9. The thickness E7 and E9 of the plies 7 and 9 is measured under pressure, ideally at the pressure corresponding to the manufacture of the textured surface insert 6.
D'autre part, plus l'épaisseur E8 du film barrière 8 sera faible et plus l'insert de surface texturée 6 restera discret en surface de la pièce de structure 1 en matière composite et n'aura pas d'influence sur les caractéristiques techniques de la pièce de structure 1 en matériau composite. A titre d'exemple, les épaisseurs des trois composants peuvent être comprises entre 0,05 et 0,5mm pour le film barrière 8 et entre 0,1 à 1mm pour les nappes 7 et 9, sans que ces exemples ne soient limitatifs. Les trois composants de l'insert de surface texturée 6, à savoir la première nappe 7, le film barrière 8 et la seconde nappe 9, sont assemblés entre eux intimement par tout procédé compatible, tel qu'un procédé mécanique par couture, agrafage, ou similaire, un procédé thermique par thermocollage, polymérisation, réticulation ou similaire, ou encore une combinaison des deux. On privilégiera un procédé thermique pour provoquer le fluage de la matière du film barrière 8 en direction des nappes 7 et 8 (tel qu'illustré schématiquement à la figure 2), et ainsi l'interpénétration du film barrière 8 dans chacune des nappes 7 et 9, liant les composants entre eux après durcissement du film barrière 8. Les conditions de ce procédé thermique en termes de température, de pression et de temps sont déterminées par l'homme du métier en fonction de la nature du film barrière 8 et font partie de ses connaissances. Lors de cette étape, la viscosité du film barrière 8 est importante. Une viscosité trop faible engendrerait des effets capillaires qui imprégneraient totalement les deux nappes 7 et 9. Elle doit donc être suffisamment élevée pour éviter ce phénomène de capillarité, et par exemple supérieure à lOOPa.s sans que cet exemple ne soit limitatif. Elle dépend à la fois de la nature du film barrière 8 et de la température de mise en œuvre, et les valeurs indiquées ne sont pas limitatives. On the other hand, the smaller the thickness E8 of the barrier film 8, the more the textured surface insert 6 will remain discrete on the surface of the composite structure part 1 and have no influence on the technical characteristics. of the structural part 1 of composite material. By way of example, the thicknesses of the three components may be between 0.05 and 0.5 mm for the barrier film 8 and between 0.1 and 1 mm for the plies 7 and 9, without these examples being limiting. The three components of the textured surface insert 6, namely the first ply 7, the barrier film 8 and the second ply 9, are joined together intimately by any compatible method, such as a mechanical method by sewing, stapling, or the like, a thermal process by heat sealing, polymerization, crosslinking or the like, or a combination of both. A thermal process will be favored to cause the material of the barrier film 8 to flow towards the plies 7 and 8 (such as schematically illustrated in Figure 2), and thus the interpenetration of the barrier film 8 in each of the layers 7 and 9, binding the components together after curing the barrier film 8. The conditions of this thermal process in terms of temperature, pressure and time are determined by the skilled person according to the nature of the barrier film 8 and are part of his knowledge. During this step, the viscosity of the barrier film 8 is important. Viscosity too low would cause capillary effects that would completely impregnate the two layers 7 and 9. It must be high enough to avoid this capillary phenomenon, and for example greater than 10OPa.s without this example being limiting. It depends at the same time on the nature of the barrier film 8 and the temperature of implementation, and the values indicated are not limiting.
L'exemple d'insert de surface texturée 6 qui vient d'être décrit n'est pas limitatif, mais a l'avantage d'être facile à industrialiser car il peut être préparé en avance et en dehors de la ligne de fabrication des pièces de structure 1 en matériau composite. De même, il peut être aisément intégré dans la pièce de structure 1 lors de sa fabrication. Il nécessite toutefois de modifier légèrement l'outillage de fabrication de ces pièces en référence à la figure 3. Une autre variante de réalisation non illustrée consiste à fabriquer un insert de surface texturée sans la seconde nappe 9 de fibres textiles et à le lier directement à la préforme de renfort de la future pièce de structure 1 en matériau composite. Cet insert de surface texturée ne comporterait que le film barrière et la première nappe de fibres textiles et serait assemblé à ladite préforme de renfort par tout procédé d'assemblage approprié, tel que par couture, aiguilletage, touffetage, ou similaire, traversant toute ou partie de l'épaisseur de la préforme de renfort, ou encore par un procédé thermique comme pour insert de surface texturée 6 décrit précédemment. La première nappe de fibres textiles pourrait ou non être complétée par les fils de renfort utilisés pour aiguilletage ou le touffetage. Ce mode de construction peut permettre d'obtenir des performances mécaniques extrêmes, mais augmente considérablement le temps de réalisation. Il peut toutefois avoir un intérêt pour des pièces de structure à forte valeur ajoutée pour des domaines exigeants comme l'aérospatial ou l'aéronautique. Dans tous les cas, l'outillage 20 permettant la fabrication d'une pièce 1 en matériau composite doit être légèrement modifié pour pouvoir intégrer insert de surface texturée 6 dans ladite pièce 1 lors de sa fabrication afin qu'il fasse partie intégrante de cette pièce et ne puisse s'en détacher. En référence à la figure 3, un outillage 20 comporte généralement au moins un moule 21 rigide et un contre moule 22 souple ou rigide (symbolisé par une flèche) définissant l'empreinte tridimensionnelle de la pièce 1 en matériau composite à fabriquer, et permettant la mise en forme d'une préforme 11 de renfort à base de fibres, l'imprégnation de la préforme 11 avec une matrice à base de polymères, puis le durcissement de la pièce 1 ainsi obtenue. Le fond du moule 21 est usiné pour créer un évidement 23 dont la forme et les dimensions correspondent à celles de la zone de jonction 3 déterminée et dont la profondeur P23 correspond sensiblement à l'épaisseur de l'insert de surface texturée 6. Une gorge 24 périphérique est usinée autour de l'évidement 23 pour y recevoir un joint d'étanchéité 25, par exemple en élastomère ou similaire, ou tout système d'étanchéité équivalent. Ce joint d'étanchéité 25 est agencé pour créer avec le rebord périphérique 10 de l'insert de surface texturée 6, lorsque le contre moule 22 est fermé sous pression, une zone d'étanchéité périphérique permettant d'isoler les fibres textiles de la première nappe 7. Ces fibres isolées restent sèches et ne sont pas ou que partiellement imprégnées par la matrice qui est injectée dans l'outillage 20 pour former avec la préforme de renfort 11 la pièce 1 en matériau composite. L'outillage 20 peut ainsi être adapté sans grand surcoût au procédé de collage selon l'invention et permet d'intégrer très facilement un ou plusieurs inserts de surface texturée 6 dans la pièce 1 à fabriquer, l'insert de surface texturée 6 n'étant pas limité ni en taille ni en surface qui peut aller de quelques mm2 à plusieurs m2. Lorsque le processus de fabrication est terminé, on obtient une pièce 1 en matériau composite dans sa définition stricte, c'est-à-dire une pièce solide monobloc, composée d'une matrice et d'une préforme de renfort 11. Seule la face extérieure de l'insert de surface texturée 6 n'est pas ou que partiellement imprégnée par la matrice, laissant apparaître les fibres sèches de la première nappe 7 dans la zone de jonction 3. La technique de texturation de surface par isolement de fibres sèches a été décrite en référence à un procédé de fabrication de pièces en matériaux composites par moulage et par injection basse pression de résine type RTM (Resin Transfert Molding). Elle peut être bien entendu transposée à pratiquement tous les procédés de fabrication de pièces en matériaux composites, même dans le cas où le contre moule n'existe pas. The example of textured surface insert 6 which has just been described is not limiting, but has the advantage of being easy to industrialize because it can be prepared in advance and outside the production line of parts of structure 1 in composite material. Similarly, it can be easily integrated into the structural part 1 during its manufacture. However, it requires slightly modifying the manufacturing tooling of these parts with reference to FIG. 3. Another variant of embodiment that is not illustrated consists in producing a textured surface insert without the second sheet 9 of textile fibers and in directly bonding it to the reinforcing preform of the future structural part 1 made of composite material. This textured surface insert would comprise only the barrier film and the first ply of textile fibers and would be assembled to said reinforcing preform by any suitable assembly method, such as stitching, needling, tufting, or the like, traversing all or part of the thickness of the reinforcing preform, or by a thermal process as textured surface insert 6 described above. The first web of textile fibers may or may not be completed by reinforcement threads used for needling or tufting. This method of construction can provide extreme mechanical performance, but increases considerably the time of realization. It may, however, have an interest in structural parts with high added value for demanding areas such as aerospace or aeronautics. In all cases, the tooling 20 allowing the manufacture of a piece 1 of composite material must be slightly modified to be able to integrate textured surface insert 6 in said piece 1 during its manufacture so that it is an integral part of this piece and can not get away from it. With reference to FIG. 3, a tooling 20 generally comprises at least one rigid mold 21 and a flexible or rigid counter mold 22 (symbolized by an arrow) defining the three-dimensional impression of the component 1 made of composite material to be manufactured, and allowing the forming a reinforcing preform 11 based on fibers, impregnating the preform 11 with a matrix based on polymers, and then hardening the part 1 thus obtained. The bottom of the mold 21 is machined to create a recess 23 whose shape and dimensions correspond to those of the junction zone 3 determined and whose depth P23 corresponds substantially to the thickness of the textured surface insert 6. A throat 24 device is machined around the recess 23 to receive a seal 25, for example elastomer or the like, or any equivalent sealing system. This seal 25 is arranged to create with the peripheral rim 10 of the textured surface insert 6, when the counter mold 22 is closed under pressure, a peripheral sealing zone for isolating the textile fibers of the first 7. These insulated fibers remain dry and are not or only partially impregnated by the matrix which is injected into the tooling 20 to form with the reinforcing preform 11 the piece 1 of composite material. The tooling 20 can thus be adapted without much extra cost to the bonding method according to the invention and makes it possible to easily integrate one or more textured surface inserts 6 in the part 1 to be manufactured, the textured surface insert 6 being not limited in size or surface that can range from a few mm 2 to several m 2 . When the manufacturing process is finished, a piece 1 of composite material is obtained in its strict definition, that is to say a solid piece made of a matrix and of a reinforcing preform 11. Only the outer face of the textured surface insert 6 is not or only partially impregnated by the matrix, leaving the dry fibers of the first sheet 7 appear in the junction zone 3. surface texturing technique by isolation of dry fibers has been described with reference to a method of manufacturing composite parts by molding and low-pressure injection resin type RTM (Resin Transfer Molding). It can of course be transposed to virtually all processes for manufacturing composite parts, even in the case where the counter mold does not exist.
Lorsque le procédé de collage de l'invention s'applique à un assemblage composite/métallique, la pièce de structure 2 métallique peut être préparée spécifiquement en effectuant une texturation de surface d'une ou de plusieurs zones de jonction 4 par ajout de matière. Elle pourrait ne pas subir une étape de texturation avant collage. On obtiendrait malgré tout un gain de résistance grâce à la texturation de la pièce composite. Pour effectuer la texturation, on utilise préférentiellement une technique de fabrication additive, par un procédé d'impression tridimensionnelle de type LMD (Laser Métal Déposition) ou similaire. Ce procédé permet d'ajouter une matière chimiquement et physiquement compatible avec le métal constituant la pièce de structure 2 pour lui permettre d'adhérer intimement à la surface de ladite pièce. La matière ajoutée peut être de préférence métallique, voire dans certains cas synthétique en fonction du procédé d'impression tridimensionnelle choisi et de la pièce 2 à texturer. When the bonding method of the invention applies to a composite / metal assembly, the metal structure part 2 can be prepared specifically by performing a surface texturizing of one or more junction zones 4 by adding material. It may not undergo a texturing step before gluing. We would still obtain a resistance gain through the texturing of the composite part. To effect the texturing, an additive manufacturing technique is preferably used, by a three-dimensional printing method of the LMD type (Laser Metal Deposition) or the like. This method makes it possible to add a material that is chemically and physically compatible with the metal constituting the structural part 2 to enable it to adhere intimately to the surface of said part. The added material may preferably be metallic, or in some cases synthetic, depending on the chosen three-dimensional printing method and the part 2 to be textured.
La figure 4 représente un exemple d'une pièce de structure 2 métallique sous la forme d'un profilé en oméga, dont les ailes d'extrémité comportent deux zones d'appui longitudinales et parallèles entre elles, formant lesdites zones de jonction 4. Ces zones de jonction 4 comportent une topographie de surface formée par des picots 12 en relief, obtenus par ajout de matière au moyen d'un procédé d'impression tridimensionnelle, ces picots 12 étant répartis uniformément. La topographie de surface peut avoir une épaisseur variable, comprise entre 0,1mm et quelques millimètres, sans que ces valeurs soient limitatives. Le motif « picot » illustré n'est pas limitatif et s'étend à tout autre motif, qui peut être déterminé en fonction des contraintes mécaniques des zones de jonction 4. Le motif d'impression tridimensionnelle peut également être choisi en fonction du dessin ou du motif de la première nappe 7 de fibres textiles, pour qu'ils soient compatibles voire complémentaires en partie ou en totalité afin d'améliorer encore l'interpénétration des deux zones de jonction 3 et 4 lors de l'opération de collage des pièces 1 et 2. Les figures 5A et 5B illustrent deux autres exemples de motif, l'un sous la forme de nervures ondulées 13 parallèles en forme de S, et l'autre sous la forme de nervures droites 14 parallèles. Ces motifs peuvent en outre être répartis uniformément ou non dans les zones de jonction 4 permettant de répartir au mieux les contraintes en fonction des modes de sollicitation rencontrés. FIG. 4 represents an example of a piece of metal structure 2 in the form of an omega section, the end flanges of which comprise two longitudinal and parallel bearing zones forming said junction zones 4. junction areas 4 comprise a surface topography formed by pins 12 in relief, obtained by adding material by means of a three-dimensional printing process, these pins 12 being distributed uniformly. The surface topography can have a variable thickness, between 0.1mm and some millimeters, without these values being limiting. The "pin" pattern illustrated is not limiting and extends to any other pattern, which can be determined according to the mechanical stresses of the junction areas 4. The three-dimensional printing pattern can also be chosen according to the drawing or the pattern of the first ply 7 of textile fibers, so that they are compatible or even complementary in part or in whole to further improve the interpenetration of the two junction areas 3 and 4 during the bonding operation of the parts 1 and Figs. 5A and 5B illustrate two further exemplary patterns, one in the form of S-shaped parallel corrugated ribs 13 and the other in the form of parallel straight ribs 14. These patterns may also be uniformly distributed or not in the junction areas 4 to distribute the best constraints according to the solicitation modes encountered.
Possibilités d'application industrielle : Possibilities of industrial application:
La figure 6 montre l'intérêt du procédé de collage selon l'invention dans une application concrète, entre une première pièce de structure 1 en matériau composite sous la forme d'une peau, et de plusieurs secondes pièces de structure 2 métalliques sous la forme de raidisseurs, assemblage courant dans le domaine de l'aéronautique et du ferroviaire par exemple. Dans cet exemple, la première pièce de structure 1 en matériau composite sort de fabrication équipée d'inserts de surface texturée 6 parfaitement intégrés, localisés dans ses zones de jonction 3, et laissant apparaître le film barrière 8 et les fibres textiles sèches de la première nappe 7. Les secondes pièces de structure 2 métallique ont subi une texturation de leurs zones de jonction 4 par impression tridimensionnelle, conformément à la figure 4. L'assemblage de ces pièces 1 et 2 par collage consiste à déposer un joint de colle 5 dans la ou les zones de jonction 3 et 4 de l'une ou des deux pièces 1 et 2, à les presser l'une contre l'autre, en les maintenant en position jusqu'au durcissement du ou des joints de colle 5. Le résultat obtenu est illustré à la figure 9 de manière très agrandie et montre un joint de colle 5 entre les deux pièces 1 et 2, et l'interpénétration des picots 12 de la zone de jonction 4 texturée de la pièce 2 métallique dans les poils 7' de la zone de jonction 3 texturée de la pièce 1 en matériau composite. FIG. 6 shows the advantage of the bonding method according to the invention in a concrete application, between a first piece of structure 1 made of composite material in the form of a skin, and several second pieces of metal structure 2 in the form of stiffeners, common assembly in the field of aeronautics and rail for example. In this example, the first structural part 1 composite material out of manufacture equipped with perfectly integrated textured surface inserts 6, located in its junction areas 3, and revealing the barrier film 8 and the dry textile fibers of the first 7. The second pieces of metal structure 2 have been texturized from their junction areas 4 by three-dimensional printing, in accordance with FIG. 4. The assembly of these parts 1 and 2 by gluing consists in depositing an adhesive joint 5 in the junction zone or zones 3 and 4 of one or both pieces 1 and 2, pressing them against each other, keeping them in position until the adhesive seam (s) 5 are hardened. The result obtained is illustrated in FIG. 9 in a very enlarged manner and shows an adhesive joint 5 between the two parts 1 and 2, and the interpenetration of the pins 12 of the zone of textured junction 4 of the metal part 2 in the bristles 7 'of the textured junction zone 3 of the piece 1 made of composite material.
Des essais sur des éprouvettes de cisaillement ont permis de valider à la fois le procédé de collage selon l'invention et son intérêt en termes d'amélioration substantielle des performances mécaniques. Selon des premiers résultats d'essais effectués sur un collage composite sur composite, on note une résistance au cisaillement moyenne de 9 Mpa pour des éprouvettes étalons réalisées avec une colle époxy et une préparation de surface standard (ponçage et dégraissage) contre une moyenne de 14 Mpa pour des éprouvettes embarquant un insert de surface texturée 6 bidimensionnel avec la même colle époxy, soit un gain de 56% de résistance en cisaillement. Tests on shear test pieces made it possible to validate both the bonding method according to the invention and its interest in terms of substantially improving the mechanical performance. According to first results of tests carried out on a composite composite bonding, we note an average shear strength of 9 MPa for standard test pieces made with an epoxy adhesive and a standard surface preparation (sanding and degreasing) against an average of 14 Mpa for specimens embedding a two-dimensional textured surface insert with the same epoxy glue, a gain of 56% in shear strength.
Il ressort clairement de cette description que l'invention permet d'atteindre les buts fixés, à savoir un procédé de collage simple à industrialiser permettant d'atteindre un haut niveau de performance mécanique, et tout particulière adapté aux assemblages composite/composite et composite/métallique, permettant ainsi de couvrir une large gamme des assemblages du marché. La présente invention n'est pas limitée aux exemples de réalisation décrits mais s'étend à toute modification et variante évidentes pour un homme du métier. It is clear from this description that the invention achieves the goals set, namely a simple bonding process to industrialize to achieve a high level of mechanical performance, and particularly suitable for composite / composite and composite / metal, thus covering a wide range of market assemblies. The present invention is not limited to the embodiments described but extends to any modification and variation obvious to a person skilled in the art.

Claims

Procédé de collage structural de pièces de structure (1, 2) dont au moins une première pièce est une pièce de structure en matériau composite (1) et une seconde pièce est une pièce de structure en matériau composite (1) ou une pièce de structure métallique (2), chaque pièce de structure en matériau composite (1) étant constituée d'une préforme de renfort (11) à base de fibres imprégnée d'une matrice à base de polymères, les deux pièces de structure (1, 2) étant assemblées entre elles lors d'une opération de collage dans laquelle on dépose un joint de colle (5) dans une zone de jonction (3, 4) déterminée d'au moins une desdites pièces de structure (1, 2), on presse lesdites pièces de structure (1, Process for the structural bonding of structural parts (1, 2), of which at least a first part is a composite material part (1) and a second part is a composite material part (1) or a structural part metal part (2), each composite material part (1) consisting of a fiber-based reinforcing preform (11) impregnated with a polymer-based matrix, the two structural parts (1, 2) being assembled together during a gluing operation in which an adhesive joint (5) is deposited in a junction area (3, 4) determined from at least one of said structural parts (1, 2), the press is pressed said structural parts (1,
2) l'une contre l'autre et on les maintient en position jusqu'au durcissement dudit joint de colle (5) pour obtenir un assemblage structurel rigide, caractérisé en ce que, préalablement à l'opération de collage, l'on effectue une texturation de surface de la zone de jonction (3) des deux pièces de structure en matériau composite (1) dans un assemblage composite/composite ou d'au moins la pièce de structure en matériau composite (1) dans un assemblage composite/métallique par ajout de matière pour augmenter la surface spécifique desdites pièces de structure (1) dans leur zone de jonction (3, 4), en ce que, pour effectuer ladite texturation de surface, on ajoute des fibres dans ladite zone de jonction 2) against each other and held in position until hardening said glue joint (5) to obtain a rigid structural assembly, characterized in that, prior to the gluing operation, is carried out surface texturing of the junction zone (3) of the two composite material structural parts (1) in a composite / composite assembly or of at least the composite material component part (1) in a composite / metallic assembly by adding material to increase the specific surface area of said structural pieces (1) in their junction area (3, 4), in that, to effect said surface texturing, fibers are added to said joining zone
(3) de chaque pièce de structure en matériau composite (1) qui ne seront pas ou que partiellement imprégnées pendant la fabrication de ladite pièce composite (1), et en ce que, lors de l'opération de collage, lorsque lesdites pièces de structure (1, 2) sont pressées l'une contre l'autre, lesdites zones de jonction (3, (3) each piece of composite material structure (1) which will not be or only partially impregnated during the manufacture of said composite part (1), and in that, during the gluing operation, when said pieces of structure (1, 2) are pressed against each other, said joining regions (3,
4) texturées s'interpénétrent et se lient intimement entre-elles avec ledit joint de colle (5) pour augmenter leur ancrage mécanique. 4) interpenetrate and intimately bond with each other with said glue joint (5) to increase their mechanical anchorage.
Procédé de collage structural selon la revendication 1, caractérisé en ce que, pour effectuer ladite texturation de surface de la zone de jonction (3) de chaque pièce de structure en matériau composite (1), l'on fabrique un insert de surface texturée (6) à base de fibres textiles dont la forme et les dimensions sont adaptées à celles de ladite zone de jonction (3), et en ce que l'on intègre ledit insert de surface texturée (6) dans chaque pièce de structure en matériau composite (1) lors de sa fabrication dans un outillage adapté, en orientant ledit insert de surface texturée (6) à l'extérieur de ladite pièce de structure en matériau composite (1) dans ladite zone de jonction (3) et en isolant les fibres textiles dudit insert de surface texturée (6) pour qu'elles restent sèches, pour qu'elles donnent une texture spécifique à ladite zone de jonction (3) et pour qu'elles soient exposées audit joint de colle Structural bonding method according to claim 1, characterized in that, to effect said surface texturing of the joining zone (3) of each piece of composite material structure (1), a textured surface insert (6) made of textile fibers is manufactured whose shape and dimensions are adapted to those of said joining zone (3), and in that that said textured surface insert (6) is incorporated in each composite material structure part (1) during its manufacture in a suitable tool, by orienting said textured surface insert (6) outside said part of a composite material structure (1) in said joining zone (3) and isolating the textile fibers of said textured surface insert (6) so that they remain dry, so that they give a texture specific to said joining zone (3) and to be exposed to said glue joint
(5) lors de l'opération de collage. (5) during the gluing operation.
Procédé de collage structural selon la revendication 2, caractérisé en ce que pour fabriquer ledit insert de surface texturée (6), l'on réalise un complexe comportant une première nappe de fibres textiles (7) superposée à un film barrière (8), ladite première nappe de fibres textiles (7) constituant une face extérieure dudit insert de surface texturée (6) agencée pour être orientée à l'extérieur de ladite pièce de structure en matériau composite (1), pour rester sèche et pour donner la texture à ladite zone de jonction (3), et ledit film barrière (8) étant agencé pour isoler la face extérieure dudit insert de surface texturée (6) par rapport à ladite pièce de structure en matériau composite (1) et pour empêcher l'imprégnation de ladite première nappe de fibres textiles (7) par la matrice dudit matériau composite pour que lesdites fibres textiles restent sèches. Structural bonding method according to Claim 2, characterized in that, in order to manufacture said textured surface insert (6), a complex comprising a first sheet of textile fibers (7) superimposed on a barrier film (8) is produced. first web of textile fibers (7) constituting an outer face of said textured surface insert (6) arranged to be oriented outside of said composite material structure part (1), to remain dry and to give texture to said junction zone (3), and said barrier film (8) being arranged to isolate the outer face of said textured surface insert (6) with respect to said composite material structure part (1) and to prevent the impregnation of said first web of textile fibers (7) by the matrix of said composite material for said textile fibers to remain dry.
Procédé de collage structural selon la revendication 3, caractérisé en ce que l'on dimensionne ledit film barrière (8) pour qu'il ait une surface (S8) supérieure à la surface (S7) de ladite première nappe de fibres textiles (7) afin de créer un rebord périphérique (10) tout autour dudit insert de surface texturée (6), ce rebord périphérique (10) étant agencé pour coopérer avec un joint d'étanchéité prévu sur ledit outillage adapté. Structural bonding method according to claim 3, characterized in that said barrier film (8) is dimensioned so that it has a surface (S8) greater than the surface (S7) of said first sheet of textile fibers (7) to create a peripheral flange (10) all around said surface insert textured (6), this peripheral flange (10) being arranged to cooperate with a seal provided on said adapted tooling.
Procédé de collage structural selon la revendication 4, caractérisé en ce que l'on assemble ledit insert de surface texturée (6) à la préforme de renfort (11) dudit matériau composite par une technique de couture, d'aiguilletage ou de touff étage. A method of structural bonding according to claim 4, characterized in that said textured surface insert (6) is assembled to the reinforcing preform (11) of said composite material by a stitching, needling or tufting technique.
Procédé de collage structural selon la revendication 4, caractérisé en ce que l'on ajoute au complexe formant ledit insert de surface texturée (6) une seconde nappe de fibres textiles (9) superposée audit film barrière (8) à l'opposé de ladite première nappe de fibres textiles (7), ladite seconde nappe de fibres textiles (9) constituant une face intérieure dudit insert de surface texturée A method of structural bonding according to claim 4, characterized in that a second web of textile fibers (9) superimposed on said barrier film (8) opposite said web is added to the complex forming said textured surface insert (6). first web of textile fibers (7), said second web of textile fibers (9) constituting an inner face of said textured surface insert
(6) agencée pour être orientée à l'intérieur de ladite pièce de structure en matériau composite (1) et pour être imprégnée par la matrice dudit matériau composite. (6) arranged to be oriented inside said composite material structure part (1) and to be impregnated by the matrix of said composite material.
Procédé de collage structural selon la revendication 6, caractérisé en ce que l'on dimensionne ladite seconde nappe de fibres textiles (9) pour qu'elle ait une surface (S9) au moins égale à la surface (S8) dudit film barrière (8). Structural bonding method according to claim 6, characterized in that said second ply of textile fibers (9) is dimensioned so that it has a surface (S9) at least equal to the surface (S8) of said barrier film (8). ).
Procédé de collage structural selon l'une quelconque des revendications 3 à 7, caractérisé en ce que l'on réalise ledit film barrière (8) dans des matières thermoplastiques ou thermodurcissables, et en ce que l'on assemble intimement ledit film barrière (8) à ladite première nappe de fibres textiles Structural bonding method according to any one of claims 3 to 7, characterized in that said barrier film (8) is made from thermoplastic or thermosetting materials, and that said barrier film (8 ) to said first web of textile fibers
(7) et/ou ladite seconde nappe de fibres textiles (9) par un procédé de thermocollage, de polymérisation ou de réticulation, sous pression, pour provoquer l'interpénétration dudit film barrière (8) dans lesdites nappes de fibres textiles (7, 9) liant les composants entre eux après durcissement dudit film barrière (7) and / or said second web of textile fibers (9) by a method of heat-sealing, polymerization or crosslinking, under pressure, to cause the interpenetration of said barrier film (8) in said webs of textile fibers (7, 9) binding the components together after curing said barrier film
(8), mais sans imprégner totalement lesdites nappes de fibres textiles (7, 9). (8), but without completely impregnating said textile fiber plies (7, 9).
9. Procédé de collage structural selon l'une quelconque des revendications 3 à 7, caractérisé en ce que l'on réalise ladite première nappe de fibres textiles (7) et/ou ladite seconde nappe de fibres textiles (9) dans des nappes bidimensionnelles obtenues à partir d'un tissu tissé ou d'un voile non tissé, et/ou dans des nappes en tridimensionnelles obtenues à partir d'un velours lisse ou côtelé, d'un tricot, d'un non-tissé aiguilleté, d'un tissu touffeté, d'un tissu gratté. 9. A method of structural bonding according to any one of claims 3 to 7, characterized in that said first web of textile fibers (7) and / or said second web of textile fibers (9) is produced in two-dimensional webs. obtained from a woven fabric or a nonwoven web, and / or in three-dimensional webs obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric, a scraped cloth.
10. Procédé de collage structural selon la revendication 1, caractérisé en ce que, dans un assemblage composite/métallique, l'on effectue en outre une texturation de surface de ladite pièce de structure en matériau métallique (2) dans ladite zone de jonction (4) en réalisant un relief tridimensionnel par ajout de matière déposée selon un procédé d'impression tridimensionnelle. 10. A method of structural bonding according to claim 1, characterized in that, in a composite / metal assembly, a surface texturing of said structural piece of metal material (2) in said junction zone is also carried out ( 4) by producing a three-dimensional relief by adding deposited material according to a three-dimensional printing process.
11. Procédé de collage structural selon la revendication 10, caractérisé en ce que l'on choisit ladite matière à déposer parmi les matières synthétiques et métalliques compatibles avec la matière métallique de ladite pièce de structure à assembler. 11. A method of structural bonding according to claim 10, characterized in that one chooses said material to be deposited among the synthetic and metallic materials compatible with the metallic material of said structural part to be assembled.
12. Procédé de collage structural selon l'une quelconque des revendications précédentes, caractérisé en ce que l'on effectue la texturation de surface des zones de jonction (3, 4) desdites pièces de structure (1, 2) à assembler en choisissant des motifs de texturation compatibles ou complémentaires. 12. A method of structural bonding according to any one of the preceding claims, characterized in that one carries out the surface texturing of the junction areas (3, 4) of said structural parts (1, 2) to be assembled by choosing compatible or complementary texturing patterns.
13. Insert de surface texturée (6) permettant la mise en œuvre du procédé de collage structural selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte un complexe pourvu d'une première nappe de fibres textiles (7) superposée à un film barrière (8), ladite première nappe de fibres textiles (7) constituant une face extérieure dudit insert de surface texturée (8) et étant agencée pour être orientée à l'extérieur de ladite pièce de structure en matériau composite (1), pour rester sèche et pour donner la texture à la zone de jonction (3) de chaque pièce de structure en matériau composite (1) (page 12, ligne 5-6), et ledit film barrière (8) étant agencé pour isoler ladite première nappe de fibres textiles (7) et pour empêcher son imprégnation par la matrice dudit matériau composite pour qu'elle reste sèche. 13. textured surface insert (6) for implementing the structural bonding method according to any one of the preceding claims, characterized in that it comprises a complex provided with a first layer of textile fibers (7) superimposed a barrier film (8), said first web of textile fibers (7) constituting an outer face of said textured surface insert (8) and being arranged to be oriented outside said structure of composite material (1), to remain dry and to give texture to the junction zone (3) of each composite material structure part (1) (page 12, line 5-6), and said barrier film ( 8) being arranged to isolate said first web of textile fibers (7) and to prevent its impregnation by the matrix of said composite material to remain dry.
14. Insert de surface texturée selon la revendication 13, caractérisé en ce que ledit film barrière (8) a une surface (S8) supérieure à la surface (S7) de ladite première nappe de fibres textiles (7) afin de créer un rebord périphérique (10) tout autour dudit insert de surface texturée (6). The textured surface insert of claim 13, characterized in that said barrier film (8) has a surface (S8) greater than the surface (S7) of said first textile fiber web (7) to create a peripheral rim (10) all around said textured surface insert (6).
15. Insert de surface texturée selon la revendication 14, caractérisé en ce qu'il comporte en outre une seconde nappe de fibres textiles (9) superposée audit film barrière (8) à l'opposé de ladite première nappe de fibres textiles (7), ladite seconde nappe de fibres textiles (9) constituant une face intérieure dudit insert de surface texturée et étant agencée pour être orientée à l'intérieur de ladite pièce de structure en matériau composite (1), pour être imprégnée par la matrice dudit matériau composite et pour lier intimement ledit insert de surface texturée (6) à ladite pièce de structure en matériau composite (1)15. textured surface insert according to claim 14, characterized in that it further comprises a second layer of textile fibers (9) superimposed on said barrier film (8) opposite said first sheet of textile fibers (7). said second web of textile fibers (9) constituting an inner face of said textured surface insert and being arranged to be oriented within said composite material structure part (1), to be impregnated by the matrix of said composite material and for intimately bonding said textured surface insert (6) to said composite material part (1)
(page 12, lignes 8- 10). (page 12, lines 8-10).
16. Insert de surface texturée selon la revendication 15, caractérisé en ce que ladite seconde nappe de fibres textiles (9) a une surface (S9) au moins égale à la surface (S8) dudit film barrière (8). Textured surface insert according to claim 15, characterized in that said second web of textile fibers (9) has a surface (S9) at least equal to the surface (S8) of said barrier film (8).
17. Insert de surface texturée selon l'une quelconque des revendications 13 à 16, caractérisé en ce que ledit film barrière (8) est réalisé dans des matières thermoplastiques ou thermodurcissables, et est assemblé intimement à ladite première nappe de fibres textiles (7) et/ou ladite seconde nappe de fibres textiles (9) par thermocollage, polymérisation ou réticulation, sous pression, pour provoquer l'interpénétration dudit film barrière (8) dans lesdites nappes de fibres textiles (7, 9) liant les composants entre eux après durcissement dudit film barrière (8), mais sans imprégner totalement lesdites nappes de fibres textiles (7, 9). Textured surface insert according to any one of claims 13 to 16, characterized in that said barrier film (8) is made of thermoplastic or thermosetting materials, and is intimately joined to said first web of textile fibers (7) and / or said second web of textile fibers (9) by heat-sealing, polymerization or crosslinking, under pressure, to cause the interpenetration of said barrier film (8) in said webs of textile fibers (7, 9) binding the components together after curing said barrier film (8), but without completely impregnating said webs of textile fibers (7, 9) .
18. Insert de surface texturée selon l'une quelconque des revendications 13 à 17, caractérisé en ce que ladite première nappe de fibres textiles (7) et/ou ladite seconde nappe de fibres textiles (9) sont réalisées dans des nappes bidimensionnelles obtenues à partir d'un tissu tissé ou d'un voile non tissé, et/ou dans des nappes tridimensionnelles obtenues à partir d'un velours lisse ou côtelé, d'un tricot, d'un non-tissé aiguilleté, d'un tissu touffeté, d'un tissu gratté. Textured surface insert according to any one of claims 13 to 17, characterized in that said first web of textile fibers (7) and / or said second web of textile fibers (9) are made in two-dimensional webs obtained from from a woven fabric or a nonwoven web, and / or in three-dimensional webs obtained from a smooth or ribbed velvet, a knit, a needle-punched nonwoven, a tufted fabric , a scraped fabric.
19. Insert de surface texturée selon la revendication 18, caractérisé en ce que ladite nappe tridimensionnelle est obtenu à partir d'un velours dont les touffes de poils sont orientées majoritairement orthogonalement par rapport au plan de ladite nappe et sont agencées pour augmenter la surface spécifique desdites pièces de structure en matériau composite (1) dans leur zone de jonction et/ou l'ancrage dudit insert dans lesdites pièces de structure en matériau composite (1). Textured surface insert according to claim 18, characterized in that said three-dimensional sheet is obtained from a pile whose pile tufts are oriented predominantly orthogonal to the plane of said sheet and are arranged to increase the specific surface area. said composite material structural parts (1) in their junction zone and / or the anchoring of said insert in said composite material structural parts (1).
20. Outillage (20) pour la fabrication d'une pièce en matériau composite (1) comportant au moins un moule (21) et un contre moule (22), ledit contre moule (22) définissant l'empreinte tridimensionnelle de ladite pièce en matériau composite (1) à fabriquer, et permettant la mise en forme d'une préforme de renfort (11) à base de fibres, l'imprégnation de la préforme avec une matrice à base de polymères, puis le durcissement de la pièce ainsi obtenue, caractérisé en ce que ledit outillage (20) est adapté pour la mise en œuvre du procédé de collage selon la revendication 4, et comporte dans ledit moule (21) au moins un évidement (23) dont la forme et les dimensions correspondent à celles de ladite zone de jonction (3) déterminée et dont la profondeur correspond à l'épaisseur dudit insert de surface texturée (6), et une gorge périphérique (24) disposée autour dudit évidement (23) pour recevoir un joint d'étanchéité (25) destiné à coopérer avec le rebord périphérique (10) dudit insert de surface texturée (6) afin d'isoler sa face extérieure et empêcher l'imprégnation de ladite première nappe de fibres textiles (7) par la matrice dudit matériau composite injectée dans ledit outillage (20) pour que les fibres textiles de ladite première nappe (7) restent sèches lors de la fabrication de ladite pièce de structure en matériau composite (1) et donnent une texture spécifique à ladite zone de jonction (3). Tooling (20) for the manufacture of a composite material part (1) comprising at least one mold (21) and a counter mold (22), said counter mold (22) defining the three-dimensional impression of said component composite material (1) to be manufactured, and allowing the shaping of a fiber-reinforced reinforcement preform (11), the impregnation of the preform with a matrix based on polymers, and then the hardening of the part thus obtained , characterized in that said tooling (20) is suitable for implementing the bonding method according to claim 4, and comprises in said mold (21) at least one recess (23) whose shape and dimensions correspond to those of said junction zone (3) determined and whose depth corresponds to the thickness of said textured surface insert (6), and a peripheral groove (24) disposed around said recess (23) to receive a seal (25) for cooperating with the peripheral rim (10) of said textured surface insert (6) for isolating its outer face and preventing the impregnation of said first web of textile fibers (7) by the matrix of said composite material injected into said tool (20) so that the textile fibers of said first web (7) remain dry during the manufacture of said composite material structure part (1) and give a texture specific to said junction zone (3).
21. Assemblage de pièces de structure (1, 2), dont au moins une première pièce est une pièce de structure en matériau composite (1) et une seconde pièce est une pièce de structure en matériau composite (1) ou une pièce de structure métallique (2), la ou les pièces de structure en matériau composite (1) étant constituée(s) d'une préforme de renfort (11) à base de fibres imprégnée d'une matrice à base de polymères, les deux pièces de structure (1, 2) étant assemblées par collage au moyen d'un joint de colle (5) dans une zone de jonction (3, 4) déterminée desdites pièces pour obtenir un assemblage structurel rigide, caractérisé en ce que lesdites pièces de structure (1, 2) sont assemblées par un procédé de collage structural selon l'une quelconque des revendications 1 à 12, en ce que la zone de jonction (3, 4) des deux pièces de structure en matériau composite (1) dans un assemblage composite/composite ou d'au moins la pièce de structure en matériau composite (1) dans un assemblage composite/métallique est texturée pour augmenter la surface spécifique desdites pièces de structure (1) dans leur zone de jonction (3) par ajout de fibres qui ne seront pas ou que partiellement imprégnées pendant la fabrication de ladite pièce composite (1), et en ce que les zones de jonction (3, 4) texturées desdites pièces de structure (1, 2) s'interpénétrent et sont liées intimement avec ledit joint de colle (5) pour augmenter leur ancrage mécanique. 21. Assembly of structural parts (1, 2), of which at least a first part is a composite material part (1) and a second part is a composite material part (1) or a structural part metal part (2), the composite material part (s) (1) consisting of a reinforcing preform (11) based on fibers impregnated with a matrix based on polymers, the two structural parts (1, 2) being bonded together by means of an adhesive joint (5) in a defined joining zone (3, 4) of said parts to obtain a rigid structural assembly, characterized in that said structural parts (1 , 2) are assembled by a structural bonding method according to any one of claims 1 to 12, in that the joining zone (3, 4) of the two composite material structural parts (1) in a composite assembly / composite or at least the structural part made of mposite (1) in a composite / metallic assembly is textured to increase the specific surface area of said structural parts (1) in their joining zone (3) by adding fibers that will not be or only partially impregnated during the manufacture of said part composite (1), and in that the textured junction regions (3, 4) of said structural parts (1, 2) interpenetrate and are intimately bonded with said glue joint (5) to increase their mechanical anchorage.
22. Assemblage de pièces de structure selon la revendication 21, caractérisé en ce que la zone de jonction (3) de la ou des pièces de structure en matériau composite (1) comporte un insert de surface texturée (6) à base de fibres textiles dont la forme et les dimensions sont adaptées à celles de ladite zone de jonction (3), ledit insert de surface texturée (6) étant intégré à chaque pièce de structure en matériau composite (1) lors de sa fabrication de sorte à être orienté à l'extérieur de ladite pièce de structure en matériau composite (1) dans ladite zone de jonction (3) et à isoler les fibres textiles dudit insert de surface texturée (6) pour qu'elles restent sèches, pour qu'elles donnent une texture spécifique à ladite zone de jonction (3) et pour qu'elles soient exposées audit joint de colle (5). 22. Assembly of structural parts according to claim 21, characterized in that the junction zone (3) of the composite structural part (s) (1) comprises a textured surface insert (6) based on textile fibers. whose shape and dimensions are adapted to those of said junction zone (3), said textured surface insert (6) being integrated into each piece of composite material structure (1) during its manufacture so as to be oriented to outside of said composite material structural part (1) in said joining zone (3) and isolating the textile fibers of said textured surface insert (6) to remain dry to give a texture specific to said junction zone (3) and to be exposed to said adhesive joint (5).
23. Assemblage de pièces de structure selon la revendication 21, caractérisé en ce que la zone de jonction (4) de ladite pièce de structure en matériau métallique23. Assembly of structural parts according to claim 21, characterized in that the junction zone (4) of said structural part made of metallic material
(2) est texturée et comporte un relief tridimensionnel par ajout de matière déposée selon un procédé d'impression tridimensionnelle. (2) is textured and has a three-dimensional relief by adding deposited material according to a three-dimensional printing method.
24. Utilisation d'un assemblage d'au moins deux pièces de structure (1, 2) selon le procédé de collage structural défini dans l'une quelconque des revendications 1 à 12 comme sous-ensemble ou ensemble structurel pour l'aéronautique, l'aérospatiale, le transport, la construction et l'énergie. 24. Use of an assembly of at least two structural parts (1, 2) according to the structural bonding method defined in any one of claims 1 to 12 as a subassembly or structural assembly for aeronautics, l aerospace, transportation, construction and energy.
EP18796858.1A 2017-10-23 2018-10-22 Method for the structural bonding of structural components, and textured-surface insert for implementing said method Pending EP3700740A1 (en)

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FR1759955A FR3072604B1 (en) 2017-10-23 2017-10-23 STRUCTURAL BONDING PROCESS OF STRUCTURAL PARTS AND BONDING INSERT FOR THE IMPLEMENTATION OF THE SAID PROCESS
PCT/EP2018/078921 WO2019081441A1 (en) 2017-10-23 2018-10-22 Method for the structural bonding of structural components, and textured-surface insert for implementing said method

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JP6057330B2 (en) * 2013-01-17 2017-01-11 日本発條株式会社 COMPOSITE MATERIAL AND METHOD FOR PRODUCING COMPOSITE MATERIAL
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